900 Series
RFM Revision
Manual:
Models:
Issued:
Reissue 3:
Revision 2:
CSP-900RFM206A-1, Rotorcraft Flight Manual
MD900 Helicopter
2 December 1994
28 January 2010
3 February 2012
FILING INSTRUCTIONS:
NOTE: Make sure that Reissue 3, Revision 1, is posted in the manual before you put in
Revision 2.
INSERT PAGES
REMOVE PAGES
FRONT MATTER:
F-i & F-ii
F-i & F-ii
F-xi thru F-xvi
F-xi thru F-xvi
F-xix thru F-xxiv
F-xix thru F-xxiv
SECTION II
2-1 thru 2-4
2-15 & 2-16
2-1 thru 2-4
2-15 & 2-16
SECTION IV
4-17 & 4-18
4-23 & 4-24
4-17 & 4-18
4-23 & 4-24
SECTION VIII
8-i & 8-ii
8-23 thru 8-26
8-29 & 8-30
8-41 thru 8-44
8-i & 8-ii
8-23 thru 8-26
8-29 & 8-30
8-41 thru 8-44
SECTION IX
9-17 & 9-18
9-17 & 9-18
SECTION X
10-i & 10-ii
10-27 & 10-28
10-i & 10-ii
10-27 & 10-28
A
900 Series
RFM Revision
This page intentionally left blank!
B
CSP−900RFM206A−1
Punch holes in circles.
European Aviation Safety Agency Approved Rotorcraft
Flight Manual for Model MD900 with PW 206A
As of 28 September 2003, the EASA began approving FAA rotorcraft
flight manuals. Operators of MD900 series helicopters registered in a
European Union member state are required to place this approval page
after the cover page in their flight manual.
Log of EASA Revisions By Date
REVISION NUMBER AND DATE
EASA Approval Number
Reissue #2, Revision 2 . . . . 31 October 2003
2177
Revision 3 . . . . . . . . . . . . . . . . . . . . 8 July 2005
2177
Revision 4 . . . . . . . . . . . . . . . . 21 August 2007
2177
Revision 5 . . . . . . . . . . . . . . 20 February 2008
2177
Revision 6 . . . . . . . . . . . . . . . . . . . 21 July 2009
2177
Reissue 3 . . . . . . . . . . . . . . . 28 January 2010
2177
Reissue 3
Cut
along dashed
EASA−i/( EASA−ii blank)
lines.
CSP−900RFM206A−1
Model MD900 with PW 206A
ROTORCRAFT
Cover
FLIGHT
MANUAL
REGISTRATION NO: _________________
SERIAL NO: _________________
F90−001A
CSP−900RFM206A−1
FAA APPROVED
ROTORCRAFT
FLIGHT MANUAL
for
Model MD900 with PW 206A
Type Certificate No. H19NM
Approved By_____________________________________
Manager, Flight Test Branch, ANM-160L
Federal Aviation Administration
Los Angeles Aircraft Certification Office
Transport Airplane Directorate
Original Approval Date: 2 December 1994
Reissue #1: 23 June 1999
Reissue #2: 26 February 2003
Reissue #3:
THE FAA APPROVED ROTORCRAFT FLIGHT MANUAL CONSISTS OF THE FOLLOWING SECTIONS.
SECTION
SECTION
SECTION
SECTION
SECTION
II −
III −
IV −
V −
X −
LIMITATIONS
EMERGENCY PROCEDURES
NORMAL PROCEDURES
PERFORMANCE DATA
OPTIONAL EQUIPMENT
Title Page
The helicopter must be operated in compliance with the operating limitations as set forth in section II of
this manual and any additional limitations from Section X as a result of an installed optional equipment
item.
Sections III, IV, V, and portions of section X contain recommended procedures and data and are FAA approved.
THIS MANUAL MUST BE KEPT IN THE HELICOPTER AT ALL TIMES.
Copyright E 1999-2010 by MD Helicopters, Inc.
All rights reserved under the copyright laws.
Original
F−i
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LOG OF REVISIONS BY DATE
FAA / NON−FAA REVISIONS
REVISION NUMBER AND DATE
Original Issue . 2 December 1994
CSP-900RFM-1
Revision 1 . . . . . . 17 April 1995
Revision 2 . . . . . . 8 August 1995
Revision 3 . . . . . . 27 September 1995
Revision 4 . . . . . . 10 October 1995
REVISION NUMBER AND DATE
Reissue #2 . . . . . 26 February 2003
This reissue replaces CSP-900RFM-1
in its entirety.
Revision 1 . . . . . . 29 May 2003
Revision 2 . . . . . . 31 October 2003
Revision 3 . . . . . . 8 July 2005
Revision 5 . . . . . . 26 June 1996
Revision 4 . . . . . . 21 August 2007
Revision 6 . . . . . . 10 July 1996
Revision 5 . . . . . . 20 February 2008
Revision 7 . . . . . . 29 October 1996
Revision 6 . . . . . . 21 July 2009
Revision 8 . . . . . . 13 November 1996
Reissue #3 . . . . . 28 January 2010
Revision 9 . . . . . . 27 January 1997
Revision 1 . . . . . . 22 July 2011
Revision 10 . . . . . 14 April 1997
Revision 2 . . . . . . 3 February 2012
Revision 11 . . . . . 14 November 1997
Revision 12 . . . . . 8 May 1998
Revision 13 . . . . . 12 August 1998
Revision 14 . . . . . 17 December 1998
Revision 15 . . . . . 2 March 1999
Reissue #1 . . . . . 23 June 1999
CSP-900RFM-1
Approved By
Manager, Flight Test Branch, ANM-160L
Federal Aviation Administration
Los Angeles Aircraft Certification Office
Transport Airplane Directorate
Revision 1 . . . . . . 1 March 2000
Revision 2 . . . . . . 22 March 2001
Revision 3 . . . . . . 30 May 2001
Revision 4 . . . . . . 02 November 2001
Revision 5 . . . . . . 18 September 2002
F−ii
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
APPROVING AUTHORITIES
Joint Aviation Authorities (JAA):
This manual was approved by the JAA.
European Aviation Safety Authority (EASA)
The MD900 and this manual were accepted by EASA based on the JAA approval
listed above. Subsequent revisions of this manual are approved by EASA who
issues a four-digit approval number. See MDHI web page http://www.mdhelicop­
ters.com, publications link for EASA approval number and instructions.
National Agency of Civil Aviation (Brazil)
This Aircraft Flight Manual is approved by the FAA on behalf of the National
Agency of Civil Aviation for Brazilian registered aircraft, in accordance with
the Regulamentos Brasileiros de Homologação Aeronáutica” (RBHA) 21, Section
21.29.
/
(Initial FAA Approval Signature/Date)
Manager, Flight Test Branch, ANM-160L
Federal Aviation Administration
Los Angeles Aircraft Certification Office
Transport Airplane Directorate
Reissue 3
Original
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CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
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Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
TABLE OF CONTENTS
PARAGRAPH
Cover . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
PAGE
1
Title Page . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F-i
Log of Revisions By Date . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F-ii
Approving Authorities . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F-iii
List of Effective Pages . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
F-vi
Section I − General
1-1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-2. Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-3. Organization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-4. Method of Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-3
1-5. Definition of Terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-3
1-6. Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-4
1-7. Multi-Purpose Utility Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-6
1-8. Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-7
1-9. Rotorcraft Certification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-10. Pilot's Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-11. Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-12. Conversion Charts and Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-11
Section II − Limitations
2-1. Flight Restrictions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-1
2-2. Environmental Operating Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-2
2-3. Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-4
2-4. Weight Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-4
2-5. Center of Gravity (CG Envelope) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-5
2-6. Rotor Brake Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-7. Rotor Speed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-8. Transmission Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-9. Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-7
2-10. Generator Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-8
2-11. Starter limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-8
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2-12. Fuel System Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-9
2-13. Integrated Instrumentation Display System (IIDS) . . . . . . . . . . . . . . . . . . . . . . .
2-10
2-14. Decals and Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-15
Section III − Emergency and Malfunction Procedures
3-1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-1
3-2. Caution and Warning Annunciators and Audio Tones . . . . . . . . . . . . . . . . . . . . . . .
3-1
3-3. Engine Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-2
3-4. Emergency Landing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-5
3-5. EEC Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-7
3-6. Engine Starting - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-11
3-7. Engine/Aircraft Shutdown - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-13
3-8. Fire Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-14
3-9. Flight Control Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-18
3-10. Pitot/Static System Malfunction: Single or Dual Pitot Tube Installation . . . . .
3-25
3-11. Engine and Generator Malfunction Indications . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-26
3-12. Transmission Malfunction Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-30
3-13. Fuel System Display Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-32
3-14. Caution and Warning Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-35
3-15. Other Malfunction/Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-39
3-16. Vibrations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-40
3-17. Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-40
3-18. Emergency Egress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-41
Section IV − Normal Procedures
4-1. Preflight Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-1
4-2. Pilot's Daily Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-4
4-3. Pilot's Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-15
4-4. Engine Pre-Start Cockpit Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-22
4-5. Engine Starting - Automatic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-24
4-6. Engine Runup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-25
4-7. Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-25
4-8. Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-26
4-9. Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-26
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CSP−900RFM206A−1
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4-10. Slow Flight/Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-26
4-11. Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-27
4-12. Engine/Aircraft Shutdown - Normal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-28
4-13. Post Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-30
4-14. Noise Impact Reduction Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-31
4-15. Flight With Doors Removed or Cabin Doors Open . . . . . . . . . . . . . . . . . . . . . . . . .
4-32
4-16. One Engine Inoperative Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-33
4-17. Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-33
Section V − Performance Data
5-1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-1
5-2. Noise Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-1
5-3. Density Altitude Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-2
5-4. Airspeed Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-4
5-5. Best Rate of Climb Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-6
5-6. Single Engine Rate of CLimb and Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-8
5-7. Twin Engine Rate of Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-11
5-8. Hover Ceiling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-19
5-9. Height Velocity Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-27
5-10. Power Assurance Check - Automatic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-28
5-11. Power Assurance Check - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-30
Section VI − Weight and Balance Data
6-1. Weight and Balance Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-1
6-2. Load Limits and Balance Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-7
6-3. Equipment Removal or Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-7
6-4. Longitudinal Weight and Balance Determination: Passenger Configuration . .
6-8
6-5. Longitudinal Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-9
6-6. Permissible Lateral Loadings - Passenger Configuration . . . . . . . . . . . . . . . . . . .
6-10
6-7. Lateral Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-11
6-8. Internal Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-11
Section VII Systems Description
7-1. Helicopter Exterior Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
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7-2. Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-3
7-3. Tailboom and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-5
7-4. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-6
7-5. Main Rotor System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-8
7-6. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-10
7-7. Hydraulic Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-19
7-8. Propulsion System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-23
7-9. Engine Air Intake and Inlet Particle Separator (IPS) . . . . . . . . . . . . . . . . . . . . . . .
7-27
7-10. Engine Power Management System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-28
7-11. Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-30
7-12. Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-33
7-13. Environmental Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-35
7-14. Integrated Instrumentation Display System (IIDS) . . . . . . . . . . . . . . . . . . . . . . .
7-37
7-15. IIDS Data Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-45
7-16. Balance Monitoring System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-48
7-17. IIDS Menu Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-49
Section VIII − Handling, Servicing and Maintenance
8-1. Hoisting, Lifting and Jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-1
8-2. Towing and Moving . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-1
8-3. Parking and Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-4
8-4. Access and Inspection Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-10
8-5. Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-21
8-6. Aircraft Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-33
8-7. Cockpit Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-34
8-8. Cabin Seats: Removal/Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-36
8-9. Copilot Flight controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-37
8-10. Engine Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-38
8-11. Special Operational Checks and Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-41
Section IX − Additional Operations and Performance Data
9-1. Abbreviated Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9-1
9-2. Fuel Flow VS Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9-4
9-3. International Civil Aviation Organization (ICAO) Noise Levels . . . . . . . . . . . . . .
9-17
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CSP−900RFM206A−1
PARAGRAPH
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Section X − Optional Equipment
10-1. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-1
10-2. Listing - Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-1
10-3. Compatibility - Combined Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-2
10-4. Optional Equipment Performance Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-3
10-5. Operating Instructions: Air Conditioning (P/N 900P7250302-101) . . . . . . . . . .
10-5
10-6. Operating Instructions: Controllable Landing/Search Light . . . . . . . . . . . . . . . .
10-9
10-7. Operating Instructions: Rotorcraft Cargo Hook Kit . . . . . . . . . . . . . . . . . . . . . . . . 10-15
10-8. Operating Instructions: Windscreen Wipers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-23
10-9. Operating Instructions: Supplemental Fuel System . . . . . . . . . . . . . . . . . . . . . . . 10-27
10-10.Operating Instructions: Rescue Hoist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-37
10-11.Operating Information: -111/-117 IIDS Option . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-51
10-12.Operating Instructions: Fire Extinguishing System . . . . . . . . . . . . . . . . . . . . . . 10-53
10-13.Operating Instructions: Smoke Detector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-57
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
SUMMARY OF REVISIONS
TO THE ROTORCRAFT FLIGHT MANUAL
NOTE: Revisions are listed below by number with appropriate remarks.
Section II pages marked [C]* indicate FAA approved color pages.
Black−and−white reproductions of color pages are not considered to be “FAA
Approved”.
REVISION
NUMBER
Revision 2
REMARKS
Section II: Paragraph 2-2. Revised operations in snow conditions.
Figure 2-15 (Sheet 2 of 2 sheets). Updated fuel system decals.
Section IV: Paragraph 4-4 and Figure 4-4. Added new strobe light
switch configuration.
Section VIII: Table 8-2. Revised Main Transmission servicing
materials.
Paragraph 8-5. Revised reference to RMM for Hydraulic System
Servicing and MIL spec for approved hydraulic fluid.
Figure 8-17. Revised transmission oil fill decal.
Paragraph 8-11. Revised first “CAUTION” and “Hydraulic System
Check”.
Revised “Dry Engine Motoring Run” procedure.
Section IX: Paragraph 9-3. Revised ICAO Noise Levels.
Section X: Paragraph 10-9. Revised fuel system placard.
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MD900 with PW 206A
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CSP−900RFM206A−1
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MD900 with PW 206A
CSP−900RFM206A−1
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CSP−900RFM206A−1
LIST OF EFFECTIVE PAGES
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LIST OF EFFECTIVE PAGES
SECTION
PAGE NUMBER
10-49
10-50
10-51
10-52
10-53
10-54
10-55
10-56
10-57
10-58
10-59
10-60
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REVISION NUMBER
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REVISION NUMBER
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
General
SECTION I
GENERAL
TABLE OF CONTENTS
PARAGRAPH
PAGE
1-1. Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-2. Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-3. Organization . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-1
1-4. Method of Presentation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-3
1-5. Definition of Terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-3
1-6. Abbreviations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-4
1-7. Multi-Purpose Utility Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-6
1-8. Technical Publications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-7
1-9. Rotorcraft Certification . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-10. Pilot's Briefing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-11. Dimensions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 1-1. MD Explorer Rotorcraft Principal Dimensions . . . . . . . . . . . . . . . . .
Figure 1-2. Interior Dimensions and Volumes . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-8
1-9
1-10
1-12. Conversion Charts and Tables . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 1-3. Speed: MPH/Knots/KmH . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 1-4. Temperature Conversion Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 1-1. Liquid Measure - U.S. Gallons to Liters . . . . . . . . . . . . . . . . . . . . .
Table 1-2. Linear Measure - Inches to Centimeters . . . . . . . . . . . . . . . . . . . . .
Table 1-3. Linear Measure - Feet to Meters . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 1-4. Weight - Pounds to Kilograms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 1-5. Conversion Chart: Knots - Meters/Second . . . . . . . . . . . . . . . . . . . .
Figure 1-6. Conversion Chart: Inches of Mercury - Millibars . . . . . . . . . . . . . .
Table 1-5. Standard Atmosphere Table . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
1-11
1-11
1-12
1-13
1-13
1-14
1-14
1-15
1-16
1-17
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MD900 with PW 206A
CSP−900RFM206A−1
General
SECTION I
GENERAL
1−1.
INTRODUCTION
The Rotorcraft Flight Manual has been prepared to provide the pilot with all informa­
tion necessary to accomplish the intended mission with the maximum amount of
efficiency and safety.
1−2.
SCOPE
This manual meets all FAA requirements for APPROVED DATA and that data
is so designated.
MD Helicopters, Inc. has included additional supplemental data which is intended
to provide the pilot with information that expands, enhances and eases his task.
1−3.
ORGANIZATION
This manual is organized in the following manner:
FRONT MATTER:
Contains: Log of Revisions by Date, Table of Contents, Summary of Revisions,
and the List of Effective Pages.
By referring to the Log of Revisions By Date, the pilot may review a chronological
listing of changes to the Flight Manual.
Reading the Summary of Revisions will inform the pilot of what changes have
been made by paragraph reference. This Summary contains only the latest Flight
Manual Change.
The List of Effective Pages allows the pilot quick reference to page numbers
and their respective revision number. The pages listed should reflect the revision
number that appears at the bottom of each page.
SECTION I - GENERAL
Information of general interest to the pilot, owner or operator of the aircraft
and general rotorcraft information and conversion charts.
SECTION II - LIMITATIONS (FAA Approved)
Specifically defines the limiting factors, procedures and parameters within which
the rotorcraft may be operated. FAA regulations require that limitations not
be exceeded.
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SECTION III - EMERGENCY AND MALFUNCTION PROCEDURES
(FAA Approved)
Problems which could be encountered in flight are defined and the procedures
necessary to cope with or alleviate them are discussed. The data is recommended
by the manufacturer.
SECTION IV - NORMAL PROCEDURES (FAA Approved)
Normal operating procedures from preflight through shutdown. The data given
is that recommended by the manufacturer.
SECTION V - PERFORMANCE DATA (FAA Approved)
Aircraft performance as defined within certain conditions, such as airspeed,
weight, altitude, temperature, humidity, and wind velocity. Data is provided in
tabular or graph form to allow the pilot to determine the aircraft's capabilities
in relation to the intended mission and prevailing conditions.
SECTION VI - WEIGHT AND BALANCE DATA
Provides aircraft weight and balance operational data in chart and table form
and provides examples that allow the pilot to accurately determine the aircraft's
gross weight, and whether the load is within longitudinal and lateral center
of gravity limits. Also contained in this section are the original weight and balance
report and equipment list (equipment both required and optional) installed on
the aircraft at the time of licensing.
SECTION VII - SYSTEMS DESCRIPTION
Offers a pilot-oriented technical description of the operation of each system
installed on the helicopter.
SECTION VIII - AIRCRAFT HANDLING, SERVICING, MAINTENANCE
AND TESTING
The information contained in this section is extracted from the Handbook of
Maintenance Instructions and is highly selective. The subjects chosen are those
with which the pilot may have direct involvement either while at his normal
base of operations or in the field.
SECTION IX - ADDITIONAL OPERATIONS AND PERFORMANCE DATA
The information provided in Section IX is given by the manufacturer to further
assist the pilot in obtaining maximum utilization of the rotorcraft. It also provides
the pilot with abbreviated checklists as well as additional performance data.
SECTION X OPTIONAL EQUIPMENT (FAA Approved)
Certain optional equipment is available for performance of specific tasks. In
many cases the equipment is removable and may be used in combination(s) with
other optional items. Whenever the installation of an option affects FAA approved
limitations, normal/emergency procedures or performance (Sections II thru V),
an FAA approval is required. In addition, a tabular listing of all options is provided
as well as a table showing the compatibility of the various options with one
another.
1−2
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MD900 with PW 206A
CSP−900RFM206A−1
General
At the front of each section there is an table of contents that lists the data by para­
graph number, title, and page number.
1−4.
METHOD OF PRESENTATION
General information in the various sections is provided in narrative form. Other
information is given in step-by-step procedures, graphs, charts, or tabular form.
The information in the step-by-step procedure is presented in the imperative mode;
each statement describing a particular operation to be accomplished. Expansion
of the steps is accomplished as follows:
l
A black change bar ( ) in the page margin designates the latest new or changed
information appearing on that page. A hand
points to changes in the contents
of an illustration.
WARNING
CAUTION
A WARNING brings to the pilot’s immediate attention that
equipment damage and/or personal injury will occur if the
instruction is disregarded − placed after the instruction/step.
A CAUTION alerts the individual that equipment damage may result
if the procedural step is not followed to the letter − placed after
the instruction/step.
NOTE: A NOTE expands upon and explains the preceding step and provides fuller
understanding of the particular operation.
1−5.
DEFINITION OF TERMS
The concept of procedural word usage and intended meaning has been adhered
to in preparing this manual is as follows:
“Shall” has been used only when the application of a procedure is mandatory.
“Should” has been used only when the application of a procedure is recommended.
“May” and “need not” have been used only when the application of a procedure
is optional.
The terms IMMEDIATELY, POSSIBLE, and PRACTICAL as used in this manual
refer to the degree of urgency with which a landing must be made.
LAND IMMEDIATELY - Execute a power-on approach and landing without delay.
LAND AS SOON AS POSSIBLE - Execute a power-on approach and landing
to the nearest safe landing area that does not further jeopardize the aircraft or
occupants.
LAND AS SOON AS PRACTICAL - Extended flight is not recommended. Whether
to complete the planned flight is at the discretion of the pilot-in-command. However,
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
the nature of the specific problem or malfunction may dictate termination of the
flight before reaching the destination.
1−6.
ABBREVIATIONS
SIGNS
>
Greater than
Equal to or greater than
<
Less than
Equal to or less than
AC
Air Conditioner
AEO
All Engines Operating
A/N
Alphanumeric
AGL
Above Ground Level
ALT
Alternate; Altitude
AOG
Aircraft On Ground
APU
Auxiliary Power Unit
ASCM
Aircraft Systems Condition
Monitoring
ATT
Attitude
BAT
Battery
BIT
Built In Test
BL
Butt Line
BLD
BMS
Centimeters
CCW
Counter Clockwise
COM
Communication
CW
Clockwise
dBA
A-weighted Decible
DIR
Direction; Directional
E
ECS
Environmental Control
System
ECTM
Engine Condition Trend
Monitoring
EEC
Electronic Engine Control
EGT
Exhaust Gas Temperature
ENG
Engine
ESNTL
Essential
ETL
Effective Translational Lift
EXT
Extend; External
F
Federal Aviation
Administration
Bleed
FADEC
Balance Monitoring
System
Full Authority Digital
Electronic Control
FAR
Federal Aviation
Regulation
FMU
Fuel Metering Unit
FSO
Flights since overhaul
Ft
Feet
Cabin
CAB HEAT Cabin Heat
CAUT
Caution
CKP(T)
Cockpit
1−4
Cm
FAA
C
CAB
Collective Lever Position
D
A
B
CLP
G
GA
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MD900 with PW 206A
General
GCU
Generator Control Unit
KIAS
Knots Indicated Airspeed
GBMC
Ground-based
Maintenance Computer
Km
Kilometer
KmH
Kilometers per Hour
GEN
Generator
KT
Knots
GPU
Ground Power Unit
KTAS
Knots True Airspeed
H
L
HD
Density Altitude
L
Left; Liters
Hg
Mercury
Lb(s)
Pound(s)
HIRF
High Intensity Radiated
Field
LND
Landing
LT
Light
HP
Pressure Altitude
HSI
Horizontal Situation
Indicator; Hot Section
Inspection
HVR
Hover
HYD
Hydraulic
M
I
MCP
Maximum Continuous
Power
M
Meters
Mbar
Millibar
Min
Minutes
MPH
Miles-Per-Hour
MSTR
Master
IAS
Indicated Airspeed
ICS
Intercom System
IFR
Instrument Flight Rules
NAV
Navigation
IGE
In Ground Effect
NG
Gas Producer RPM
IIDS
Integrated Instrumentation
Display System
NP
Power Turbine RPM
NR
Rotor Speed
N
IMC
Instrument Meteorological
Conditions
In
Inches
INST
Instrument
INST(R)
O
OAT
Outside Air Temperature
OEI
One Engine Inoperative
OGE
Out of Ground Effect
Instrument
OVRD
Override
IPS
Inlet Particle Separator
OVSP
Overspeed
IVSI
Instantaneous Vertical
Speed Indicator
K
KG
P
PLA
Power Lever Angle
PMA
Permanent Magnet
Alternator
Kilogram
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
V
PNL
Panel
POSN
Position
PRI
Primary
R
R
Right
REL
Release
RET
Retract
RTR
Rotor
S
Sec
Seconds
SEL
Sound Exposure Level
SL
Sea Level
SLT
Searchlight
SSO
Starts since overhaul
STA
Station
STBY
Standby
STC
Supplemental Type
Certificate
SYS
System
VFR
Visual FLight Rules
VH
Maximum speed in level
flight at MCP
VLV
Valve
VMC
Visual Metrological
Conditions
VNE
Never Exceed Speed
Vs
Versus
VSCS
Vertical Stabilization
Control System
VY
Best Rate of Climb Speed
U
U.S. gal
W
WL
T
TBO
Time Between Overhaul
TOP
Takeoff Power
TSN
TSO
1−7.
U.S. gallons
Water Line
X
XFD
Crossfeed
Time Since New
XMSN
Transmission
Time Since Overhaul
XPNDR
Transponder
MULTI−PURPOSE UTILITY OPERATIONS
The installation and use of certain optional equipment is approved by the FAA
and requires supplemental flight data when limitations, performance or procedures
are affected. Refer to Section X for Optional Equipment.
MD Helicopters, Inc. Helicopter optional equipment items and STC items which
are FAA approved for the MD EXPLORER may be installed and used.
1−6
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MD900 with PW 206A
1−8.
CSP−900RFM206A−1
General
TECHNICAL PUBLICATIONS
A file of technical publications is available to aid in obtaining maximum utilization
of your rotorcraft. Revisions and new issue publications are provided to continually
update and expand existing data.
MDHI Publications Revisions and Reissues
Changes in limitations, procedures, performance, optional equipment, etc., re­
quire flight manual revisions and change or replace flight manual content as
appropriate. To ensure that MDHI manuals continue to show current changes,
revised information is supplied as follows.
Revisions
Change to parts of the manual by the replacement, addition and/or deletion
of pages is done by revision. The List of Effective Pages that accompanies
each revision, identifies all affected pages. Such pages must be removed from
the manual and discarded. Added or replaced pages must be put in and ex­
amined against the List of Effective Pages.
Reissues
Occasionally the manual may be reissued and is identified as ``Reissue #1,
Reissue #2'', etc. The preceding issue of the manual then becomes obsolete
and must be discarded. The reissue includes all prior revisions. All pages
in a reissue become ``Original'' pages. The reissue may also include new or
changed data. These changes will be identified on the ``Summary of Revisions''
page.
The following publications are available.
Rotorcraft Flight Manual (RFM).
Rotorcraft Maintenance Manual (RMM)
Servicing and Maintenance
Instruments - Electrical - Avionics
Component Maintenance Manual (CMM)
Structural Repair Manual (SRM)
Illustrated Parts Catalog (IPC)
Service Information Bulletins and Letters
New and revised publications are available through MDHS Subscription Service.
Further information may be obtained by contacting:
MD Helicopters, Inc.
M615-G048
5000 E McDowell Rd
Mesa, AZ 85215
or your local Service Center, Distributor, or Sales Company.
All persons who fly or maintain MD helicopters are urged to keep abreast of the
latest information by using the subscription service.
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General
1−9.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ROTORCRAFT CERTIFICATION
Certified under FAR Part 27 through amendment 27-26 dated April 5, 1990, and
Special Condition for High Intensity Radiated Fields (HIRF) protection per FAR
21.16; FAR Part 36 Appendix J, Noise, effective on the date of Type Certification.
The rotorcraft is certified by the Federal Aviation Administration under FAA Type
Certificate Number H19NM.
The FAA model designation is MD900
The FAA/ICAO aircraft type designator is EXPL
The MD Helicopters, Inc. commercial designation is MD Explorer
1−10. PILOT’S BRIEFING
Prior to flight, passengers should be briefed on the following.
Approach and depart the rotorcraft from the front in full view of the pilot, being
aware of the main rotor.
Use of seat belts and shoulder harnesses.
Smoking.
The opening and closing of doors.
Evacuation of the aircraft in an emergency.
Location and use of emergency/survival equipment.
1−11. DIMENSIONS
Dimensions
Refer to Figure 1-1 and Figure 1-2 for exterior dimensions and interior volumes.
1−8
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MD900 with PW 206A
General
33.83 FT
(10.34 M)
5.33 FT
(1.62 M)
5.92 FT
(1.80 M)
40.58 FT
(12.37 m)
9.33 FT
5 ° 0'
9.17 FT
(2.79 M)
12.00 FT
(3.66 M)
10.92 FT
(3.33 M)
3 ° 16' STATIC GROUND LINE
@ DESIGN GROSS WEIGHT
7.33 FT
(2.23 M)
34.08 FT
(10.39 M)
F90−002B
Figure 1−1. MD Explorer Rotorcraft Principal Dimensions
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
6.25 FT (1.9 M)
4.75 FT (1.4 M)
12.9 FT (3.9 M)
18.25 FT (5.5 M)
BAGGAGE COMPARTMENT
51.4 FT3 (1.5 M3)
4.08 FT (1.2 M)
ENTIRE AFT CABIN
172.5 FT3 (4.9 M3)
4.16 FT (1.2 M) WITH DOOR ON
4.33 FT (1.3 M) WITH DOOR OFF
Figure 1−2. Interior Dimensions and Volumes
1−10
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MD900 with PW 206A
CSP−900RFM206A−1
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1−12. CONVERSION CHARTS AND TABLES
EXAMPLE: CONVERT 100 KNOTS TO MPH AND TO KM/HR:
ENTER CHART AT 100 KNOTS AND FOLLOW ARROW TO SLOPING LINE. TO FIND MPH, MOVE LEFT AND READ
115 MPH. TO FIND KM/HR, MOVE RIGHT FROM THE SLOPING LINE AND READ 185 KM/HR
200
320
300
180
280
260
160
240
140
220
200
120
100
160
Km/H
MPH
180
140
80
120
100
60
80
40
60
40
20
20
0
0
0
20
40
60
80
100
120
140
160
180
KNOTS
F05−002
Figure 1−3. Speed: MPH/Knots/KmH
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TEMPERATURE
°F
EXAMPLE:
CONVERT °F TO °C
KNOWN:
TEMPERATURE = 50° F
140
60
120
50
100
40
80
60
METHOD:
ENTER AT 50° F
READ 10° C ACROSS ON °C SCALE
40
20
METHOD MAY BE REVERSED
TO FIND ° F WHEN ° C IS KNOWN
0
ALTERNATE METHOD:
° F = (9/5 X °C) + 32
°C = 5/9(°F − 32)
°C
30
20
10
0
−10
−20
−20
−30
−40
−40
−60
−50
−80
−60
F05−003
Figure 1−4. Temperature Conversion Chart
1−12
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
General
Table 1−1. Liquid Measure − U.S. Gallons to Liters
U.S.
0
Gallons
Liters
0
1
2
3
4
5
6
7
8
9
Liters
Liters
Liters
Liters
Liters
Liters
Liters
Liters
Liters
−
3.785
7.571
11.356
15.142
18.927
22.713
26.498
30.283
34.069
10
37.854
41.640
45.425
49.211
52.996
56.781
60.567
64.352
68.138
71.923
20
75.709
79.494
83.280
87.065
90.850
94.636
98.421
102.21
105.99
109.78
30
113.56
117.35
121.13
124.92
128.70
132.49
136.28
140.06
143.85
147.63
40
151.42
155.20
158.99
162.77
166.56
170.34
174.13
177.92
181.70
185.49
50
189.27
193.06
196.84
200.63
204.41
208.20
211.98
215.77
219.56
223.34
60
227.13
230.91
234.70
238.48
242.27
246.05
249.84
253.62
257.41
261.19
70
264.98
268.77
272.55
276.34
280.12
283.91
287.69
291.48
295.26
299.05
80
302.83
306.62
310.41
314.19
317.98
321.76
325.55
329.33
333.12
336.90
90
340.69
344.47
348.26
352.05
355.83
359.62
363.40
367.19
370.97
374.76
100
378.54
382.33
386.11
389.90
393.69
397.47
401.26
405.04
408.83
412.61
Table 1−2. Linear Measure − Inches to Centimeters
Inches
0
1
2
3
4
5
6
7
8
9
Cm
Cm
Cm
Cm
Cm
Cm
Cm
Cm
Cm
Cm
0
−
2.54
5.08
7.62
10.16
12.70
15.24
17.78
20.32
22.86
10
25.40
27.94
30.48
33.02
35.56
38.10
40.64
43.18
45.72
48.26
20
50.80
53.34
55.88
58.42
60.96
63.50
66.04
68.58
71.12
73.66
30
76.20
78.74
81.28
83.82
86.36
88.90
91.44
93.98
96.52
99.06
40
101.60
104.14
106.68
109.22
111.76
114.30
116.84
119.38
121.92
124.46
50
127.00
129.54
132.08
134.62
137.16
139.70
142.24
144.78
147.32
149.86
60
152.40
154.94
157.48
160.02
162.56
165.10
167.64
170.18
172.72
175.26
70
177.80
180.34
182.88
185.42
187.96
190.50
193.04
195.58
198.12
200.66
80
203.20
205.74
208.28
210.82
213.36
215.90
218.44
220.98
223.52
226.06
90
228.60
231.14
233.68
236.22
238.76
241.30
243.84
246.38
248.92
251.46
100
254.00
256.54
259.08
261.62
264.16
266.70
269.24
271.78
274.32
276.86
Reissue 3
Original
1−13
CSP−900RFM206A−1
General
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 1−3. Linear Measure − Feet to Meters
0
1
2
3
4
5
6
7
8
9
Meters
Meters
Meters
Meters
Meters
Meters
Meters
Meters
Meters
Meters
0
−
0.305
0.610
0.914
1.219
1.524
1.829
2.134
2.438
2.743
10
3.048
3.353
3.658
3.962
4.267
4.572
4.877
5.182
5.466
5.791
20
6.096
6.401
6.706
7.010
7.315
7.620
7.925
8.229
8.534
8.839
30
9.144
9.449
9.753
10.058
10.363
10.668
10.972
11.277
11.582
11.887
40
12.192
12.496
12.801
13.106
13.411
13.716
14.020
14.325
14.630
14.935
50
15.239
15.544
15.849
16.154
16.459
16.763
17.068
17.373
17.678
17.983
60
18.287
18.592
18.897
19.202
19.507
19.811
20.116
20.421
20.726
21.031
70
21.335
21.640
21.945
22.250
22.555
22.859
23.164
23.469
23.774
24.070
80
24.383
24.688
24.993
25.298
25.602
25.907
26.212
26.517
26.822
27.126
90
27.431
27.736
28.041
28.346
28.651
28.955
29.260
29.565
29.870
30.174
100
30.479
30.784
31.089
31.394
31.698
32.003
32.308
32.613
32.918
33.222
Feet
Table 1−4. Weight − Pounds to Kilograms
0
1
2
3
4
5
6
7
8
9
Pounds
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
Kilograms
0
−
0.454
0.907
1.361
1.814
2.268
2.722
3.175
3.629
4.082
10
4.536
4.990
5.443
5.897
6.350
6.804
7.257
7.711
8.165
8.618
20
9.072
9.525
9.979
10.433
10.886
11.340
11.793
12.247
12.701
13.154
30
13.608
14.061
14.515
14.969
15.422
15.876
16.329
16.783
17.237
17.690
40
18.144
18.597
19.051
19.504
19.958
20.412
20.865
21.319
21.772
22.226
50
22.680
23.133
23.587
24.040
24.494
24.948
25.401
25.855
26.308
26.762
60
27.216
27.669
28.123
28.576
29.030
29.484
29.937
30.391
30.844
31.298
70
31.751
32.205
32.659
33.112
33.566
34.019
34.473
34.927
35.380
35.834
80
36.287
36.741
37.195
37.648
38.102
38.555
39.009
39.463
39.916
40.370
90
40.823
41.277
41.730
42.184
42.638
43.091
43.545
43.998
44.453
44.906
100
45.359
45.813
46.266
46.720
47.174
47.627
48.081
48.534
48.988
49.442
1−14
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
General
KNOTS
METERS/SEC
50
25
45
40
20
EXAMPLE
35
CONVERT KNOTS TO METERS/SEC
KNOWN:
WIND SPEED = 25 KT
30
METHOD:
ENTER CHART AT 25 KT READ
APPROXIMATELY 13 METERS/SEC
ACROSS ON METERS/SEC SCALE
25
METHOD MAY BE REVERSED
TO FIND KNOTS WHEN METERS/SEC ARE
KNOWN
20
15
10
15
10
5
5
0
0
F90−003
Figure 1−5. Conversion Chart: Knots − Meters/Second
Reissue 3
Original
1−15
CSP−900RFM206A−1
General
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
EXAMPLE 1: 29.44 IN. Hg = 997 mbar
EXAMPLE 2: 30.18 IN. Hg = 1022 mbar
29.5
29.4
1
29.3
29.2
31.1
30.4
31.0
30.3
30.9
30.2
29.1
30.8
2
30.1
29.0
IN. Hg
30.5
30.7
30.0
28.9
30.6
29.9
28.8
30.5
29.8
28.7
1035
1040
1045
1050
1055
29.7
28.6
29.6
28.5
29.5
28.4
1000
28.3
1005
1010
1015
1020
1025
1030
1035
28.2
28.1
28.0
945
950
955
960
965
970
975
980
985
990
995
1000
MILLIBARS
F90−004
Figure 1−6. Conversion Chart: Inches of Mercury − Millibars
1−16
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
General
Table 1−5. Standard Atmosphere Table
Standard Sea Level Conditions:
Temperature:
59°F (15°C)
Pressure:
29.921 in.Hg (1013.25 mbar)
Density:
0.0023769 slugs/ft3 (1.225 kg/m3)
DENSITY
RATIO σ
1
σ
0
1.0000
1.000
1000
0.9711
2000
ALTITUDE
(feet)
TEMPERATURE
(°F)
PRESSURE
(mbar)
PRESSURE
(in. Hg)
PRESSURE
RATIO
15.00
59.000
1013.25
29.921
1.0000
1.0148
13.019
55.434
997.18
28.856
0.9644
0.9428
1.0299
11.038
51.868
942.14
27.821
0.9298
3000
0.9151
1.0454
9.056
48.302
908.14
26.817
0.8962
4000
0.8881
1.0611
7.076
44.735
875.12
25.842
0.8637
5000
0.8617
1.0773
5.094
41.196
843.08
24.896
0.8320
6000
0.8359
1.0938
3.113
37.603
811.99
23.978
0.8014
7000
0.8106
1.1107
1.132
34.037
781.86
23.088
0.7716
8000
0.7860
1.1279
-0.850
30.471
752.63
22.225
0.7428
9000
0.7620
1.1456
-2.831
26.905
724.29
21.388
0.7148
10000
0.7385
1.1637
-4.812
23.338
696.82
20.577
0.6877
11000
0.7155
1.1822
-6.793
19.772
670.21
19.791
0.6614
12000
0.6932
1.2011
-8.774
16.206
644.40
19.029
0.6360
13000
0.6713
1.2205
-10.756
12.640
619.44
18.292
0.6113
14000
0.6500
1.2403
-12.737
9.074
595.23
17.577
0.5875
15000
0.6292
1.2606
-14.718
5.508
571.83
16.886
0.5643
16000
0.6090
1.2815
-16.669
1.941
549.14
16.216
0.5420
17000
0.5892
1.3028
-18.680
-1.625
527.23
15.569
0.5203
18000
0.5669
1.3246
-20.662
-5.191
505.99
14.942
0.4994
19000
0.5511
1.3470
-22.643
-8.757
485.48
14.336
0.4791
20000
0.5328
1.3700
-24.624
-12.323
465.63
13.750
0.4595
21000
0.5150
1.3935
-26.605
-15.899
446.47
13.184
0.4406
22000
0.4976
1.4176
-28.587
-19.456
427.91
12.636
0.4223
23000
0.4806
1.4424
-30.568
-23.002
409.99
12.107
0.4046
24000
0.4642
1.4678
-32.549
-26.588
392.72
11.597
0.3874
25000
0.4481
1.4938
-34.530
-30.154
375.99
11.103
0.3711
(°C)
Reissue 3
Original
1−17
CSP−900RFM206A−1
General
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
1−18
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Limitations
SECTION II
LIMITATIONS
TABLE OF CONTENTS
PARAGRAPH
PAGE
2-1. Flight Restrictions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-1
2-2. Environmental Operating Conditions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-1. Ambient Temperature Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-2. WAT Limit and “Area A” Azimuth For Crosswind Operations . . .
2-2
2-2
2-3
2-3. Airspeed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-3. VNE Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-4
2-4
2-4. Weight Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-4. Minimum Flying Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-4
2-5
2-5. Center of Gravity (CG Envelope) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-5. Center of Gravity Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-5
2-5
2-6. Rotor Brake Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-7. Rotor Speed Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-8. Transmission Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-6
2-9. Power Plant Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-7
2-10. Generator Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-8
2-11. Starter limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-8
2-12. Fuel System Limitations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 2-1. Fuel Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-9
2-9
2-13. Integrated Instrumentation Display System (IIDS) . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-6. Primary IIDS Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-7. NP and NR Scales at 100% NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-8. NP and NR Scales at 104% NP . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-9. Engine Torque . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-10. Engine Exhaust Gas Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-11. Secondary IIDS Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-12. Engine Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 2-13. Transmission and Fuel Quantity Display . . . . . . . . . . . . . . . . . . . .
Figure 2-14. Airspeed Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
2-10
2-10
2-11
2-11
2-12
2-12
2-13
2-13
2-14
2-14
FAA Approved
Reissue 3
Original
2−i
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PARAGRAPH
PAGE
2-14. Decals and Placards . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15
Figure 2-15. Decals and Placards (Sheet 1 of 2 Sheets) . . . . . . . . . . . . . . . . . . . . 2-15
Figure 2-15. Decals and Placards (Sheet 2 of 2 Sheets) . . . . . . . . . . . . . . . . . . . . . 2-16
2−ii
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Limitations
SECTION II
LIMITATIONS
2−1.
FLIGHT RESTRICTIONS
Approved as an eight place (maximum) helicopter.
The minimum flight crew consists of one pilot operating the helicopter from the
right seat. The left crew seat may be used for an additional pilot when the approved
dual controls are installed.
Under seat baggage stowage:
Placing of cargo or baggage under seats (including crew seats) is permitted only
when the seat is unoccupied.
Aerobatic flight:
Aerobatic flight is not allowed.
Aircraft equipped with Bendix/King KFC900 Flight Control System:
NOTE: The following information supersedes applicable limitations found in Bendix/King
IFR Avionics/KFC 900 RFMS 006−00845−0000 for STC SR00436WI−D.
For VFR flights at gross weights between 6251 and 6500LB:
Maximum airspeed with autopilot engaged is 100 KIAS
Maximum Operating Altitude with autopilot engaged 5000 FT HD
For IFR flights at gross weights between 6251 and 6500LB:
Autopilot must be operational.
Maximum airspeed with autopilot engaged is 100 KIAS
Maximum Operating Altitude with autopilot engaged 5000 FT HD
Flight with doors opened or removed is approved under the following
conditions.
Baggage door removed:
With the baggage door removed and cockpit and cabin doors closed, maximum
airspeed is limited to the 140 KIAS envelope shown in Figure 2-3.
Approved doors off configurations:
Maximum airspeed is limited to the 100 KIAS envelope shown in Figure 2-3.
Both cockpit doors removed
Both cabin doors removed
Both cockpit and both cabin doors removed
Cabin doors open in flight:
Maximum airspeed is limited to 60 KIAS (with or without cockpit doors).
One or both cabin doors may be opened or closed in flight at airspeeds up
to 60 KIAS.
Maximum airspeed is limited to 100 KIAS (with or without cockpit doors)
following installation of modified upper door fittings (Ref. Figure 2-14). For
sustained flight with the cabin doors open, use of the cabin door hold open
device is required.
NOTE: Baggage compartment door may be removed with any of the above
configurations.
FAA Approved
Reissue 3
Original
2−1
CSP−900RFM206A−1
Limitations
2−2.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENVIRONMENTAL OPERATING CONDITIONS
Kinds of Operations:
This rotorcraft is certified in the normal helicopter category for day and night
VFR operation when the appropriate instruments and equipment required by
the airworthiness and/or operating rules are approved, installed and are in oper­
able condition.
Maximum operating altitude at gross weights 6250 LBS and below:
20,000 Feet HD
Maximum operating altitude at gross weights 6251 to 6500 LBS:
14,000 Feet HD.
Maximum altitude for HIGE/takeoff and landing operations: Refer to
Figure 2-2.
20000
PRESSURE ALTITUDE - FEET
18000
14000 HD LIMIT FOR
GROSS
WEIGHTS
FROM 6251 TO 6500 LB
16000
14000
12000
10000
8000
6000
4000
2000
0
-50
-40
-30
-36
-20
-10
0
10
20
FREE AIR TEMPERATURE - °C
30
40
50
52
F90−010D
Figure 2−1. Ambient Temperature Envelope
IIDS Built In Test - cold temperature:
A commanded IIDS BIT must be performed prior to the first start of the day
if the helicopter has been statically exposed to temperatures below 0°C for 12
hours or longer.
NOTE: The IIDS display may not be readable during the initial power up BIT when
statically exposed to the above ambient temperatures.
Cabin heat:
Cabin heat must be OFF in the crew and passenger compartments when ambient
temperatures are greater than 28°C (82°F).
Icing conditions:
Flight into known icing conditions is prohibited.
2−2
FAA Approved
Reissue 3
Revision 2
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Snow conditions:
VNE is 100 KIAS in falling and blowing snow.
Aircraft with NACA inlet and IPS only.
Flight into falling or blowing snow is only permitted with the NACA inlet
switch in the closed position. The switch shall remain in the closed position
for the duration of the flight, even after leaving the falling or blowing snow
conditions.
MAXIMUM SAFE WINDS FOR HOVER OPERATIONS DECREASE WITH
INCREASING DENSITY ALTITUDE. TAKEOFF AND LANDING OPERATIONS IN
CALM WINDS OR HEADWINDS
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏÏ
12400
12000
11000
10000
DENSITY ALTITUDE - FEET
OBSERVE THE MAXIMUM WEIGHT,
ALTITUDE, TEMPERATURE (WAT)
LIMITS FOR TAKEOFF AND LANDING
IGE HOVER OPERATIONS HAVE BEEN
DEMONSTRATED IN WINDS UP TO 17 KNOTS
FROM ANY AZIMUTH.
9000
8000
7000
IGE
HOVER
OPERATIONS
HAVE
BEEN
DEMONSTRATED IN WINDS UP TO 17 KNOTS FROM
ALL AZIMUTHS EXCEPT BETWEEN 120 AND 135
AND
IGE
HOVER
OPERATIONS
HAVE
BEEN
DEMONSTRATED IN WINDS UP TO 15 KNOTS FOR
AZIMUTHS BETWEEN 120 AND 135.
6000
5000
4000
3000
AVOID STEADY IGE HOVER OPERATIONS IN AREA A WHEN WINDS ARE
GREATER THAN 15 KNOTS FROM AZIMUTHS BETWEEN 120 TO 135.
2000
1000
0
4000
4200
4400
4600
4800
5000
5200
5400
5600
5800 6000
6250
6500
6200 6400
6600
GROSS WEIGHT - LBS
120°
AZIMUTH RANGE FOR AREA A
135°
F90−112D
Figure 2−2. WAT Limit and “Area A” Azimuth For Crosswind Operations
FAA Approved
Reissue 3
Revision 2
2−3
CSP−900RFM206A−1
Limitations
2−3.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AIRSPEED LIMITATIONS
Observe gross weight depictions on chart.
VNE is 60 KIAS with lateral C.G. greater than +2 inches.
VNE is 134 KIAS at 6500 LBS following compliance with SB900-105.
VNE decreases at a rate of 4 kts/1000 FT above 5500 Feet HD
20000
100 KIAS
ENVELOPE
DENSITY ALTITUDE - FEET
: VNE DUE TO
TIP MACH
VNE : POWER ON
VNE: -25°C
15000
: HD AND VNE
LIMIT FOR 6251
TO 6500LB
-36°C
10000
-30°C
VNE: AUTOROTATION
OEI OPERATIONS
HYDRAULICS FAILURE
VSCS FAILURE
NP BEEP FAILURE
5000
5100 - 6250LB
<5100 LB
0
40
50
60
70
80
90
100
110
INDICATED AIRSPEED - KNOTS
120
ÏÏÏ
ÏÏÏ
ÏÏÏ
ÏÏÏ
ÏÏÏ
ÏÏÏ
130
140 150
134
140 KIAS
ENVELOPE
F92−019B
Figure 2−3. VNE Chart
2−4.
WEIGHT LIMITATIONS
If SB900-099R1 and SB900-102R1 have been accomplished: Maximum gross weight
6500 pounds.
If only SB900-099R1 has been accomplished: Maximum gross weight 6250 pounds.
If SB900-099R1 and SB900-102R1 have not been accomplished: Maximum gross
weight 5400 pounds.
Minimum flying gross weight: Refer to Figure 2-4.
Cargo deck capacity: 1500 lb. not to exceed 115 lbs. per square foot.
Maximum weight in baggage compartment (sta. 234 to 257): 500 lb. not to exceed
115 lb per square foot.
2−4
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
DENSITY ALTITUDE - FEET
20000
4000
2000
1153
0
-2000
-4000
-6000
-6812
-8000
3500
3000
4000
4185
GROSS WEIGHT - LB
F90-161A
Figure 2−4. Minimum Flying Weight
2−5.
CENTER OF GRAVITY (CG ENVELOPE)
Ensure helicopter CG and weight are within approved limits throughout flight.
Expanded lateral C.G.:
Maximum lateral C.G. for takeoffs and landings from/to a surface is + 2 inches.
VNE is 60 KIAS with lateral C.G. greater than +2 inches.
Longitudinal C.G. envelope is as shown on chart “B” below when lateral C.G.
is greater than +2 inches.
6500
6500
WHEN OPERATING IN THE
EXPANDED CG REGION OF
CHART A, THE MAXIMUM
LONGITUDINAL C.G. LIMIT,
AS DEPICTED BY THE
DASHED LINE IN CHART B,
APPLIES.
5500
EXPANDED
CG LIMITS
5000
6000
5100 LBS
5500
5000
4500
4500
4000
4000
3500
3500
3000
−3
−2
−1
0
1
2
3
4
CHART A: LATERAL C.G. STATION (IN.)
5
6
7
194
196
198
200
202
204
206
GROSS WIGHT − LBS
GROSS WIGHT − LBS
6000
3000
208
CHART B: LONGITUDINAL C.G. STATION (IN)
F92−011C
Figure 2−5. Center of Gravity Envelope
FAA Approved
Reissue 3
Original
2−5
CSP−900RFM206A−1
Limitations
2−6.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ROTOR BRAKE LIMITATIONS
The rotor brake must be in the stowed position prior to engine starting.
The rotor brake may be applied after both engines are shutdown with NR at or
below 70 percent.
2−7.
ROTOR SPEED LIMITATIONS
Power on:
Continuous operation
100 KIAS:
Maximum 105%
Minimum 99%
Continuous operation
> 100 KIAS:
Maximum 101%
Minimum 99%
91% to 108%
Transient Range:
NOTE:
Normal Operating Range: > 47 KIAS
47 KIAS
99% to 101%
103% to 105%
Power off:
Continuous operation:
2−8.
108% maximum
88% minimum
TRANSMISSION LIMITATIONS
Maximum transmission oil pressure: 104% PSI
Minimum transmission oil pressure: See Figure 2-13
Maximum transmission oil temperature: 110°C
Minimum transmission oil temperature: -18°C
2−6
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
2−9.
CSP−900RFM206A−1
Limitations
POWER PLANT LIMITATIONS
The pilot shall monitor the IIDS during all phases of operation and
record and report any exceedances to maintenance as soon as
possible.
CAUTION
Any time a limit is exceeded, the exceeded limit shall be reported to maintenance
as soon as possible.
Torque limits:
Normal:
Maximum continuous (for all flight conditions): 100%
Maximum transient over torque: 110% for 10 seconds
OEI limits:
Maximum continuous: 100%
2.5 minutes: 101% to 130%
Exhaust gas temperature limits:
Normal limits:
Maximum continuous: 820°C
Takeoff (5 minute) 821°C to 863°C
Transient limits: 863°C to 925°C for 5 seconds
OEI limits:
Maximum continuous: 863°C
2.5 minute 864°C to 902°C
Maximum transient limits: 903°C to 940°C for 20 seconds
Overtemperature limits for starting:
760°C for 2 seconds maximum
Output shaft (NP) speed limits:
Continuous operation
100 KIAS:
Maximum 104.5%
Continuous operation
> 100 KIAS:
Maximum 104.5%
Transient Range:
104.5% to 112.4% for 20 seconds
(not cumulative)
NOTE:
Normal Operating Range: > 47 KIAS
47 KIAS
FAA Approved
Reissue 3
Original
99.5% to 100.5%
103.5% to 104.5%
2−7
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NG limitations:
Maximum continuous: 98.7%
Overspeed limit: 103% for 20 seconds
OEI operating limits:
Maximum continuous: 98.7%
Up to 101%: 2.5 minutes
Engine oil system limitations:
Engine oil temperature limits:
During starting: -36°C to 110°C
Continuous: 10°C to 110°C
Engine oil pressure limits:
Normal operating range: 85 to 112% psi
Maximum: >112% psi for more than 10 minutes
Minimum: <80% psi
2−10. GENERATOR LIMITATIONS
Maximum continuous: 99% for each generator.
2−11. STARTER LIMITATIONS
30 seconds on, 30 seconds off; 30 seconds on, 30 seconds off; 30 seconds on, 30 minutes
off.
2−8
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Limitations
2−12. FUEL SYSTEM LIMITATIONS
Fuels conforming to the types listed in Table 2-1 are approved for use. Additional
fuel specifications may be found in Section VIII.
Table 2−1. Fuel Specifications
Kerosene: Jet A, A−1, A−2, JP8,
RT(2),
FUEL TYPE
TS-1(1)(2)
Wide Cut: Jet B, JP4
High Flash: JP5
(1).Use of TS-1 is limited by P&WC to not more than 1000 hours (intermittently or con­
tinuously) between engine fuel nozzle inspections.
(2).Must contain one of the following anti-ice additives at a concentration up to 0.3% by
volume: Ethylene Glycol Monomethyl Ether (Ethylcellosolve, Liquid I) as defined in
GOST 8313, Liquid I-M (mixture 50% Liquid I with 50% methyl alcohol) as defined in
TU-6-10-1458, Tetrahydrofurfuryl alcohol (TGF) as defined in GOST 17477 or Liquid
TGF-M (mixture 50% TGF with 50% methyl alcohol ) as defined in TU 6-10-1457.
Additional fuel specifications may be found in Section VIII.
WARNING
Maximum 140 KIAS with low fuel warning tick marks on.
During operations in temperatures of 13F (-10C) or colder, fuel added to the tank
must contain either anti-icing additive PFA‐55MB or anti-icing additive per
MIL‐I‐27868 or MIL‐I‐85470 with a minimum concentration of .06% by volume and
a maximum concentration of .15% by volume. Follow manufacturer's instructions.
FAA Approved
Reissue 3
Original
2−9
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
2−13. INTEGRATED INSTRUMENTATION DISPLAY SYSTEM (IIDS)
EXHAUST GAS
TEMPERATURE DISPLAY
ENGINE TORQUE
DISPLAY
. . . . . . . . . . . . . . .
. . . . . . . . . . . . . . .
DIGITAL
DISPLAYS
TORQUE
NR
NP
NP
EGT
ENG
OUT
.
POWER TURBINE
SPEED DISPLAY
EEC
MAN
FAIL
.
EEC
MAN
FAIL
ROTOR SPEED DISPLAY
F90−012
Figure 2−6. Primary IIDS Display
2−10
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NP
NR
NR
NP
NP
>111%
>112%
>108%
>108%
>102%
98 - 102%
>101%
99 - 101%
<99%
<98%
<91%
<88%
<80%
NOTE: > = GREATER THAN
< = LESS THAN
F90−013−1
Figure 2−7. NP and NR Scales at 100% NP
NP
NR
NR
NP
NP
>111%
>112%
>108%
>108%
>105%
>105%
103 - 105%
<103%
103 - 105%
<103%
<91%
<88%
<82%
NOTE: > = GREATER THAN
< = LESS THAN
F90−013−2
Figure 2−8. NP and NR Scales at 104% NP
FAA Approved
Reissue 3
Original
2−11
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NORMAL
OPERATIONS
100% and 104% NR
TORQUE
OEI OPERATIONS
TORQUE
>110%
>130%
>100%
>100%
>98%
>98%
EEC
MAN
FAIL
EEC
MAN
FAIL
NOTE: > = GREATER THAN
< = LESS THAN
F90−014
Figure 2−9. Engine Torque
EGT
EGT
>863°C
>902°C
ENG
OUT
ENG
OUT
>820°C
.
.
>863°C
.
>815°C
.
>858°C
NORMAL
OPERATIONS
OEI OPERATION
ONLY
NOTE: > = GREATER THAN
< = LESS THAN
F90−015
Figure 2−10. Engine Exhaust Gas Temperature
2−12
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LEFT ENGINE PARAMETER
DISPLAY
TRANSMISSION OIL TRANSMISSION PARAMETER RIGHT ENGINE PARAMETER
DISPLAY
PRESSURE DISPLAY
DISPLAY
ENGINE OIL
TEMPERATURE DISPLAY
FIRE
FIRE
FIRE
CHIPS
CHIPS
CHIPS
CAB HEAT
BAT HOT
ENGINE OIL
PRESSURE DISPLAY
BAT WRM
° C %PSI
° C %PSI
° C %PSI
FUEL
TRANSMISSION OIL
TEMPERATURE DISPLAY
%LOAD
GEN
%LOAD
GEN
ROTOR
BRAKE
CABIN
DOOR
BAGGAGE
DOOR
1 HYD 2
GENERATOR
%LOAD DISPLAY
IIDS
NG
NG
LB
GAS PRODUCER
TURBINE SPEED DISPLAY
OAT ° C
FUEL QUANTITY
F90−016
Figure 2−11. Secondary IIDS Display
FIRE
CHIPS
HIGH WARNING: 110°C
HIGH CAUTION: 105°C
LOW CAUTION: 10°C
° C %PSI
>112% PSI
TIME
>10 MINUTES
<80% PSI
<80% PSI
TIME
>2 SEC
>5 SEC
CAUTION: 100% LOAD
%LOAD
GEN
HIGH WARNING: 101% NG
HIGH CAUTION: 98% NG
NOTE: > = GREATER THAN
< = LESS THAN
NG
LOW WARNING: 50% NG
F90−017
Figure 2−12. Engine Display
FAA Approved
Reissue 3
Original
2−13
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FIRE
CHIPS
HIGH WARNING: 110°C
HIGH CAUTION: 93°C
HIGH WARNING: 104% PSI
HIGH CAUTION: 100% PSI
°C %PSI
LOW CAUTION: -18°C
FLIGHT
IDLE
LOW CAUTION: <75% PSI NONE
LOW WARNING: <65% PSI <50% PSI
FUEL
LOW FUEL WARNING
SEGMENT: 150 LBS
LOW CAUTION: 300 LBS
LOW FUEL WARNING TICK MARK: 97 TO 117 LBS
LB
F90−018
Figure 2−13. Transmission and Fuel Quantity Display
KNOTS
200
MPH
180
AIRSPEED INDICATOR MARKINGS:
ÎÎ
ÎÎ
150 KNOTS
100 KNOTS
0-30kt INDICATOR UNRELIABLE
160
40
200 AIRSPEED
140
150
40
60
ÎÎ
ÎÎ
ÎÎ
100
120
80
60
100
F90−020
Figure 2−14. Airspeed Indicator
2−14
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Limitations
2−14. DECALS AND PLACARDS
SEAT ATTACH
ONLY
NO TIEDOWN
LOCATED AT UPPER CABIN
SEAT ATTACH POINTS
FUEL CELL ACCESS DOOR
WARNING
LOCATED ON CABIN FLOOR
REPLACE DOOR BEFORE FLIGHT
AND JACKING AIRCRAFT
WARNING
THIS PANEL MUST BE SECURED
PRIOR TO JACKING, TOWING
OR FLYING THE AIRCRAFT
NO ARTICLES TO BE
STOWED UNDER SEATS
LOCATED ON BAGGAGE
COMPARTMENT FLOOR
LOCATED ON COCKPIT DOOR
LOWER WINDOW FRAME
1. LOCATED ON UPPER
COCKPIT DOOR FRAME
2. LOCATED ADJACENT
TO COCKPIT DOOR
ACCESS HANDLE
SLIDING
DOOR
NO ARTICLES TO BE
STOWED UNDER SEATS
PRIOR TO FLIGHT
1.
2.
TURN HANDLE TO SAFELOCK POSITION
FASTEN SEAT BELTS AND SHOULDER HARNESS
EMERGENCY EXIT
PULL TAB
TO REMOVE WINDOW
LOCATED ON CABIN DOOR
UPPER FRAME (FWD)
LOCATED ON CABIN DOOR
UPPER FRAME (CENTER)
LOCATED ON CABIN DOOR
UPPER FRAME (AFT)
LOCATED ON CABIN DOOR FRAME
ADJACENT TO EMERGENCY EXIT
RELEASE HANDLE
F90−051B
Figure 2−15. Decals and Placards (Sheet 1 of 2 Sheets)
FAA Approved
Reissue 3
Original
2−15
CSP−900RFM206A−1
Limitations
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
DURING OPERATIONS IN TEMPERATURES OF 40F (4C)
OR COLDER, FUEL ADDED TO THE TANK MUST CONTAIN
EITHER ANTI-ICING ADDITIVE PFA-55MB OR ANTI-ICING
ADDITIVE PER MIL-I-27868 OR MIL-I-85470 WITH A
MINIMUM CONCENTRATION OF .06% BY VOLUME
AND A MAXIMUM CONCENTRATION OF .15% BY VOLUME.
SEE FLIGHT MANUAL FOR MIXING PROCEDURES.
THIS HELICOPTER MUST BE OPERATED
IN COMPLIANCE WITH THE OPERATING
LIMITATIONS SPECIFIED IN THE FAA
APPROVED ROTORCRAFT FLIGHT MANUAL
LOCATED ON INSTRUMENT PANEL
APPROVED FOR
VFR DAY/NIGHT
LOCATED ON INSTRUMENT PANEL
LOCATED ABOVE FUEL FILLER
RADIO CALL
N X X X X X
LOCATED ON INSTRUMENT PANEL
VNE CHART: LOCATED ON INSTRUMENT PANEL
LOCATED ABOVE FUEL FILLER
USEABLE CAP. 158.5 U.S. GALS (600 LITERS)
WITH RANGE EXTENDER INSTALLED
USEABLE CAP. 158.5 U.S. GALS
WITH RANGE EXTENDER INSTALLED
LOCATED ON FILLER NECK
ROTOR
BRAKE
LIFT HANDLE,
ROTATE CW,
PULL DOWN
NO STEP
LOCATED ON FILLER NECK
DO NOT
ENGAGE ROTOR
BRAKE ABOVE
70% NR
LOCATED ADJACENT TO ROTOR BRAKE
STATIC PORT
KEEP HOLES AND
SURFACE CLEAN
100 KT
CAPABILITY
LOCATED ABOVE STATIC PORT
MODIFIED FITTING WITH DECAL
F90−113E
Figure 2−15. Decals and Placards (Sheet 2 of 2 Sheets)
2−16
FAA Approved
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
S E C T I O N III
EMERGENCY AND MALFUNCTION
PROCEDURES
TABLE OF CONTENTS
PARAGRAPH
PAGE
3-1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-1
3-2. Caution and Warning Annunciators and Audio Tones . . . . . . . . . . . . . . . . . . . . . . .
3-1
3-3. Engine Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Single Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Second Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Low Rotor RPM Warning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-4. Emergency Landing Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Water Landing - Dual Engine Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Water Landing - OEI/AEO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-5. EEC Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-1. EEC Caution/Warning Annunciators . . . . . . . . . . . . . . . . . . . . . . . . .
EEC Critical Fault . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EEC Non Critical Fault . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EEC Manual Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-6. Engine Starting - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-2
3-2
3-4
3-4
3-5
3-5
3-5
3-7
3-7
3-7
3-8
3-10
3-11
3-7. Engine/Aircraft Shutdown - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-13
3-8. Fire Emergencies . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cabin Fire/Smoke . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Electrical Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-2. Engine/Transmission Deck Fire Annunciators . . . . . . . . . . . . . . . . .
Engine FIRE - On Ground . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine FIRE - During Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Transmission Area Fire . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-9. Flight Control Malfunctions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Anti-Torque Failure - General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Anti-Torque Failure - Complete Loss of Thrust . . . . . . . . . . . . . . . . . . . . . . . . . . .
Anti-Torque Failure - Fixed Thruster Setting . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-14
3-14
3-15
3-16
3-16
3-17
3-17
3-18
3-18
3-19
3-21
FAA Approved
Reissue 3
Original
3−i
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PARAGRAPH
PAGE
VSCS Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23
Figure 3-3. VSCS Indicator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23
Hydraulic System Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-24
Cyclic Trim Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-24
Collective Friction Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25
3-10. Pitot/Static System Malfunction: Single or Dual Pitot Tube Installation . . . . . 3-25
Static System Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25
Figure 3-4. Alternate Static Source Toggle Valve . . . . . . . . . . . . . . . . . . . . . . . . . 3-25
3-11. Engine and Generator Malfunction Indications . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-5. Engine and Generator Malfunction Annunciators . . . . . . . . . . . . . .
Engine High Oil Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Low Oil Temperature . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine High Oil Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Low Oil Pressure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Chips . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
NG High . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
NG Low . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Generator High Load . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Generator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-12. Transmission Malfunction Indications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-6. Transmission Malfunction Annunciators . . . . . . . . . . . . . . . . . . . . . .
Transmission Oil Temperature High . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Transmission Oil Temperature Low . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Transmission Oil Pressure Low . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Transmission Oil Pressure High . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Transmission Chips . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-13. Fuel System Display Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-7. Fuel System Advisory Indicators . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Low . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Boost Pump Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Crossfeed Valve Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Single Fuel Probe Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Dual Fuel Probe Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Impending Fuel Filter bypass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Fuel Shutoff Valve Malfunction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-14. Caution and Warning Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-8. Caution/Warning Cluster . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Cabin Heat . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Battery Hot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Battery Warm . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3−ii
FAA Approved
Reissue 3
Original
3-26
3-26
3-26
3-27
3-27
3-27
3-28
3-28
3-28
3-29
3-29
3-30
3-30
3-30
3-31
3-31
3-31
3-31
3-32
3-32
3-33
3-33
3-33
3-34
3-34
3-34
3-35
3-35
3-35
3-36
3-36
3-37
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
PARAGRAPH
PAGE
Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-38
Baggage Door . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-38
IIDS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-38
3-15. Other Malfunction/Advisories . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39
IIDS Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39
NP Switch Failure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39
IPS Bypass . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39
Battery Discharge . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-39
3-16. Vibrations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-40
3-17. Emergency Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-9. Emergency Fire Extinguisher . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-40
3-40
3-18. Emergency Egress . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 3-10. Cabin Door Emergency Exit . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
3-41
3-41
FAA Approved
Reissue 3
Original
3−iii
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
3−iv
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
SECTION III
EMERGENCY AND
MALFUNCTION PROCEDURES
3−1.
GENERAL
The procedures contained in this section are to be followed in the event of an emergen­
cy or malfunction that may potentially affect the safety of the aircrew, passengers,
aircraft, or personnel on the ground.
These procedures are recommended to minimize danger to the helicopter. However,
these procedures should not limit the pilot from taking additional actions if the
situation warrants.
In the event of an emergency or malfunction, the pilot's primary consideration
is control of the aircraft. Then, the pilot must identify the problem and perform
the appropriate procedures relevant to the situation.
Terms such as ``land immediately'', ``land as soon as possible'', and ``land as
soon as practical'' are defined in Section I.
3−2.
CAUTION AND WARNING ANNUNCIATORS AND AUDIO TONES
A red warning or yellow caution annunciator will illuminate on the IIDS display
and in some cases, an audio warning will sound announcing a failure or malfunction.
Some secondary IIDS displays have a digital display with a corresponding caution/
warning annunciator. Pilots should insure that both the digital display and its ap­
propriate caution/warning annunciator are in agreement before executing the proper
emergency procedure. If they do not agree, other parameters should be cross‐checked
in an attempt to validate a given abnormal indication.
The following logic applies to the warning advisories:
1. ENG OUT, FIRE, CAB HEAT, and LOW FUEL warning tick marks flash
(only go OFF if condition that caused the warning goes away).
2. All other warnings turn ON continuously (only go OFF if condition that caused
the warning goes away).
FAA Approved
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Audio warnings alert the pilot through the headset that a malfunction has occurred
that may require immediate corrective action.
The warning tone: The warning tone will sequence a high and low tone twice
to indicate a warning condition. These tones are activated for FIRE, CAB HEAT,
BAT HOT, and EEC FAIL.
Low Rotor Audio tone: The low rotor RPM tone (a sweep tone) is activated for
rotor RPM less than 95% and either engine operating, or activated for rotor
RPM less than 88% and both engines failed. When the IIDS senses an engine
failure, the low rotor RPM tone is activated for one cycle. The audio tones are
disabled when the aircraft is on the ground.
3−3.
ENGINE EMERGENCIES
The ENG OUT warning annunciator is located between the TORQUE and EGT
vertical displays. When the IIDS senses an engine failure, the ENG OUT
TORQUE
warning flashes and the low rotor RPM tone is activated
EGT
for one cycle. The EGT and TORQUE displays also reENG
scale. The ENG OUT advisory is disabled with aircraft
OUT
on the ground.
SINGLE ENGINE FAILURE
Indications: ENG OUT annunciator illuminated and low rotor tone ON for one cycle.
Affected engine torque, NP and NG decreasing to zero.
Procedures:
Conditions: At a hover - IGE:
Land
Conditions: At a hover - OGE:
ADJUST TO MAINTAIN OEI LIMITS
Collective pitch
NOTE: The decision to land or fly−away, following a single engine failure, will depend
on ambient conditions and aircraft gross weight. Refer to Section V for best rate
of climb speed, single engine rate of climb and descent, and height velocity
envelope performance data.
3−2
FAA Approved
Reissue 3
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
Conditions: In flight:
Maintain operating engine within OEI limits
Reduce airspeed to 100 kts or less (Ref. Section II)
CAUTION
Identify affected (failed) engine by cross checking torque, NP and
NG prior to performing following steps.
Engine control switch
OFF ON AFFECTED ENGINE
Fuel shutoff valve
OFF ON AFFECTED ENGINE
NOTE: If attempting a restart leave fuel shutoff valve ON. Do not attempt restart if a
malfunction is suspected.
Crossfeed valve
Land as soon as practical
ON
NOTE: If cabin heat or air-conditioning is being used when an engine failure occurs it
will automatically be switched OFF to enable the pilot to utilize the maximum
available power from the remaining engine for a safe recovery. If, after
recovering to a safe OEI flight condition, cabin heat is needed for windscreen
defogging, cabin comfort, etc., select the CAB HEAT OVRD position to restore
cabin heat. Prior to the OEI landing, insure CAB HEAT is OFF to ensure that the
maximum power is available from the remaining engine.
Air start:
Failed engine control switch
TO OFF THEN TO FLY
IIDS
MONITOR
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND ENGINE FAILURE
Indications: Low rotor RPM with low rotor tone ON if RPM is below 88%.
Possible left yaw
Torque, NP, and NG decreasing to zero.
Procedures:
Lower collective and maintain rotor speed within limits
Perform autorotation to suitable landing area.
LOW ROTOR RPM WARNING
Procedures:
Adjust collective as necessary to control rotor RPM.
WARNING
3−4
Respond immediately to the ENGINE OUT/low rotor RPM warning
by adjusting collective to maintain rotor RPM within limits, then
check engine instruments and other indications to confirm engine
trouble.
FAA Approved
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−4.
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
EMERGENCY LANDING PROCEDURES
WATER LANDING - DUAL ENGINE FAILURE
Procedures:
Adjust collective pitch as necessary to establish autorotation.
Cabin doors may be opened when airspeed is 60 KIAS or less.
Make autorotative approach, flaring as required to minimize forward speed
at touchdown.
Level aircraft. Increase collective pitch as contact is made with the water.
When aircraft begins to roll, lower collective to full down to minimize blades
skipping off the water.
Notify crew/passengers to evacuate aircraft after blades have stopped turning.
WARNING
Do not inflate personal flotation gear until clear of the aircraft −
safe exit will be restricted.
WATER LANDING - OEI/AEO
Conditions: Available power allows hovering.
NOTE: The gross weight of the aircraft will determine whether sufficient power is
available to terminate the approach at a hover or whether a run−on landing must
be performed if landing OEI.
Procedures:
Establish normal approach to intended landing point.
Cabin doors may be opened when airspeed is 60 KIAS or less.
Plan to arrive at 100 FT above touchdown at approximately 40 KIAS.
At approximately 50 FT, enter a decelerating attitude and increase power to
reduce rate of closure.
Descend to hovering altitude over water.
Passengers and copilot exit aircraft.
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Fly a safe distance away from all personnel in the water to avoid injury.
Place ENGINE CONTROL switch(s) in OFF and perform a hovering autorota­
tion.
Allow aircraft to settle in a level attitude while applying full collective pitch.
When aircraft begins to roll, reduce collective to full down to minimize blades
skipping off the water.
Release safety harness and exit the aircraft as soon as the blades have stopped
turning.
WARNING
Do not inflate personal flotation gear until clear of the aircraft −
safe exit will be restricted.
Conditions: Available power does not allow hovering.
Procedures:
Establish normal approach to intended landing point.
Cabin doors may be opened when airspeed is 60 KIAS or less.
Plan to arrive at 100 FT above touchdown at approximately 40 KIAS.
At approximately 50 FT, enter a decelerating attitude and increase power to
reduce rate of closure.
As water contact is made, shut down engine and hold the helicopter as level
as possible, keeping forward speed and rate of descent to a minimum.
When aircraft begins to roll, reduce collective to full down to minimize blades
skipping off the water.
Release safety harness and exit the aircraft as soon as the blades have stopped
turning.
WARNING
3−6
Do not inflate personal flotation gear until clear of the aircraft −
safe exit will be restricted.
FAA Approved
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−5.
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
EEC MALFUNCTIONS
TORQUE
EEC NON CRITICAL FAULT
CAUTION ANNUNCIATOR
( YELLOW)
EEC
MAN
FAIL
EEC
MAN
FAIL
EEC MANUAL MODE
ANNUNCIATOR (YELLOW)
EEC CRITICAL FAULT WARNING
ANNUNCIATOR (RED)
F90−021
Figure 3−1. EEC Caution/Warning Annunciators
NOTE: The pilot should attempt to reset the EEC by by slightly moving the affected
engine’s twistgrip out of the NORMAL detent, pressing the EEC RESET button,
and returning the twistgrip to NORMAL. Two attempts may be required. If the
EEC malfunction indication clears, the EEC was experiencing a transient fault.
If the EEC malfunction indication remains ON, the fault condition is still present
and the appropriate malfunction procedure should be followed.
EEC CRITICAL FAULT
Indications: EEC with FAIL warning annunciator ON and activation of the warning tone
for two cycles.
In the event that the EEC on one of the engines fails, the fuel flow of that engine
remains fixed and can only be controlled by the twistgrip. The engine with the
serviceable EEC will attempt to maintain NP/NR within limits.
Procedures:
If necessary, move the affected engine twist grip out of the NORMAL position
to assume manual control of the FMU.
NOTE: The pilot has the option of leaving the fuel flow fixed or using the throttle twist grip
to adjust the fuel flow (torque). When either twist grip is taken out of the NORMAL
position, the EEC MAN annunciator will illuminate. Changes in power will be
compensated through the serviceable EEC engine from zero torque to
temperature limits. Twist grip movement is only required for large power
changes.
FAA Approved
Reissue 3
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
CAUTION
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
When operating at 104% NR, reductions in power that allow the
torque on the engine in the automatic mode to approach zero %
can lead to an increase in N P on the engine being manually
controlled into the transient (20 second time limit) overspeed range
illuminated). If conditions permit or,
(> 104.5% − first yellow
when operating in a training environment, it is recommended that
the NR be set to 100% to provide a greater margin prior to entering
a transient NP overspeed range.
Set power of the affected engine as desired.
Continue flight and monitor engine indications on the IIDS primary display.
CAUTION
There is no NR governing following EEC failures on both engines.
NR and power must be controlled by the pilot using a combination
of collective and twistgrips.
EEC NON CRITICAL FAULT
An EEC caution annunciator ON in flight may result in one of the following indica­
tions.
Indications: Engine torque matching may be degraded.
Conditions: At 100% NP
Procedures:
Continue flight
NP switch
Avoid right quartering tailwinds during
landing
Advise maintenance
LEAVE IN NORM FOR DURATION
OF FLIGHT
Conditions: At 104% NP
Procedures:
3−8
Continue flight
NP switch
Advise maintenance
NORM AND LEAVE IN NORM FOR
DURATION OF FLIGHT
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
Indications: EGT indication blanks
Conditions: In flight
Procedures:
Continue flight
Advise maintenance
Conditions: On ground prior to starting
Procedures:
Do not attempt start, or abort start.
Advise maintenance
Indications: Inability to change engine mode with engine control switch.
Conditions: In flight
Procedures:
Continue flight
After landing, perform manual engine shutdown (Ref. paragraph 3-7).
Conditions: On ground after landing
Procedures:
Perform manual engine shutdown (Ref. paragraph 3-7).
FAA Approved
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Indications: NP and NR indications not matched (split)
Conditions: In flight
Procedures:
Continue flight
Avoid maneuvers that cause NR to increase above normal. (High rates of de­
scent, quick stops)
Conditions: On ground
Procedures:
Do not takeoff
Advise maintenance
EEC MANUAL CONTROL
Indications: EEC and MAN annunciator ON
Procedures:
EEC RESET switch
PRESS
Twistgrips
CHECK IN NORMAL DETENT
Indications: EEC annunciator flashing. The EEC is in automatic, but one of the twist grips
is not in the normal position.
Procedures:
3−10
RETURN TO NORMAL POSITION
Twist grip
FAA Approved
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−6.
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ENGINE STARTING − MANUAL
NOTE: The following procedure is provided to the pilot as a means of starting an engine
after experiencing an EEC FAIL warning which would preclude a normal
automatic start. Flight with one EEC failed (one engine manually controlled)
should be considered an abnormal procedure. It should only be done to
evacuate the helicopter from a hazardous environment or, if necessary, for a
return flight to a maintenance base where repairs can be performed. Before
attempting a start and flight with an EEC FAIL warning on one engine, pilots
should be familiar with the information in paragraphs 3−5 thru 3−7.
NOTE: To enable the starter to function during a manual start with an EEC FAIL
warning, it may be necessary for a second crew member to push and hold
the appropriate Engine Manual Start Button located on the back corners
of the electrical load center (Ref. Section VII).
NOTE: Complete the Engine Prestart cockpit check (Section IV) before attempting a
manual start.
Collective control:
NOTE: The following steps of rotating the twist grip to reset the PLA are not required if
the engine was previously shut down utilizing the manual shutdown procedures
in paragraph 3−7. Insure the twist grip is in the OFF position.
Twistgrip on selected engine
SLOWLY ROTATE TO FULL OPEN
(PAST THE ‘‘NORMAL’’ DETENT):
THIS RESETS THE PLA
Off gate release switch
PRESS AND HOLD
Twist grip on selected engine
SLOWLY ROTATE TO OFF
Off gate release switch
RELEASE
Electrical master panel:
Fuel system panel:
Engine control panel:
Generator on selected engine
L BOOST or R BOOST for appropriate
engine
ON, CHECK IIDS INDICATIONS
IDLE
L ENGINE or R ENGINE
CAUTION
OFF
Monitor EGT, NG, and starter limits during start. Abort the start
If EGT rises rapidly through 700°C.
FAA Approved
Reissue 3
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3−11
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Abort start procedure:
Off gate release switch
PRESS AND HOLD
Twistgrip on selected engine
OFF
Engine control panel switch
OFF WHEN EGT IS BELOW 150°C
NOTE: If the starter does not engage after placing the engine control switch in IDLE, the
EEC may have detected a non critical fault. Return engine control switch to OFF
and recycle the electrical power switch. Recycling aircraft power clears the fault
and will allow the start.
ROTATE TOWARDS NORMAL
Twist grip for selected engine
NOTE: As NG increases through 8% rotate twistgrip toward normal until lightoff occurs.
Observe EGT indication for immediate temperature rise. Monitor EGT and NG
during start. Increase twistgrip toward normal only as necessary to keep NG
accelerating toward idle. Manually bring NP/NR to 65%.
CAUTION
If lightoff is not attained with an increase of EGT and NG within
10 seconds, rotate the twistgrip to OFF and place the engine control
switch to off. Following a 30 second fuel drain period, perform a
30 second dry motoring run (Ref. Section VIII) before attempting
another start. Repeat the complete starting sequence observing
limitations.
Engine oil pressure
CHECK
Generator
ON
IIDS
CHECK
GPU start only:
Generators
ON
GPU
DISCONNECT
3−12
FAA Approved
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−7.
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ENGINE/AIRCRAFT SHUTDOWN − MANUAL
NOTE: This procedure may be performed in the event a normal shutdown cannot be
accomplished on one or both engines.
Collective stick
FULL DOWN
Cyclic stick
TRIM TO NEUTRAL
Pedals
NEUTRAL
Twist grip(s)
IDLE
NOTE: Earlier configuration with OFF GATE: The idle position is not marked on the
twist grips. Idle is located at the point where the twist grip can no longer be rotated
toward the OFF position.
Current configuration without OFF GATE:
The idle position is not marked on the twist grips. At a point between NORMAL
and OFF, the twistgrip will no longer be able to be rotated to OFF without applying
additional force (aproximately 30 to 40 LBS).
Utility panel:
Fuel system panel:
Electrical master panel:
NP(s) slows to idle
CHECK
EEC MAN indication(s) on primary IIDS
display
CHECK
Engine control panel:
Earlier configuration with OFF GATE:
OFF GATE release switch
PRESS AND HOLD
Twistgrip(s)
SNAP TO CUTOFF
OFF GATE release switch
RELEASE
All unnecessary bleed air and electrical
equipment
OFF
OFF
L/R BOOST
OFF
L/R GEN
OFF
L ENGINE or R ENGINE
FAA Approved
Reissue 3
Original
3−13
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Current configuration without OFF GATE:
SNAP TO CUTOFF
Twistgrip(s)
NOTE: At a point between NORMAL and OFF, the twistgrip will no longer be able to be
rotated to OFF without applying additional force (aproximately 30 to 40 LBS).
CHECK NORMAL SHUTDOWN
INDICATIONS
IIDS
Continue with normal shutdown procedures
3−8.
FIRE EMERGENCIES
CABIN FIRE/SMOKE
Indications: Smoke and fume accumulation in the cabin.
Conditions: On ground
Procedures:
Engine control switches
OFF
Passengers/crew
EVACUATE
Rotor brake (if installed)
APPLY
Power switch
OFF
Conditions: In flight
Procedures:
Cabin heat
OFF (if source of smoke is the
cabin heat duct)
Fresh air vents
OPEN
AC/VENT switch
VENT LOW OR VENT HIGH
NOTE: If crew station and/or passenger compartment gaspers appear to be the source
of smoke and or fumes, the AC/VENT switch should remain OFF or be returned
to OFF.
Cockpit door vents
Land immediately
3−14
OPEN
FAA Approved
Reissue 3
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
After landing:
Engine control switch
OFF FOR OPERATING ENGINE
Rotor brake (if installed)
APPLY
Power switch
OFF
Passengers/crew
EVACUATE
ELECTRICAL FIRE
Indications: Smoke and fume accumulation in the cabin.
Conditions: On ground
Procedures:
Engine control switches
OFF
Passengers/crew
EVACUATE
Rotor brake (if installed)
APPLY
Power switch
OFF
Conditions: In flight
Procedures:
Cabin heat
OFF
Fresh air vents
OPEN
Generator switches
OFF
If smoke/fire conditions persist:
Land as soon as possible.
After landing:
Engine control switches
OFF
Rotor brake (if installed)
APPLY
Power switch
OFF
Passengers/crew
EVACUATE
ESNTL
POWER switch
FAA Approved
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CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LEFT ENGINE FIRE WARNING
ANNUNCIATOR (RED)
TRANSMISSION DECK FIRE
WARNING ANNUNCIATOR (RED)
RIGHT ENGINE FIRE WARNING
ANNUNCIATOR (RED)
FIRE
FIRE
FIRE
CHIPS
CHIPS
CHIPS
F90−022
Figure 3−2. Engine/Transmission Deck Fire Annunciators
ENGINE FIRE - ON GROUND
Indications: Engine FIRE warning annunciator ON and activation of the warning tone for
two cycles.
Procedures:
Engine control switches
OFF BOTH ENGINES
Rotor brake (if installed)
APPLY
Fuel shutoff valve
OFF FOR AFFECTED ENGINE
Fuel boost pumps
OFF
Attempt to confirm existence of fire
Fire bottle switch (if installed)
PRI (ALT IF NECESSARY)
NOTE: Fire bottle will not discharge with fuel shutoff valve ON.
Power switch
OFF
Passengers/crew
EVACUATE
3−16
FAA Approved
Reissue 3
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ENGINE FIRE - DURING FLIGHT
Indications: Engine FIRE warning annunciator ON and activation of the warning tone for
two cycles.
Procedures:
REDUCE TO O.E.I. VNE OR LESS
Airspeed
Attempt to confirm existence of fire
NOTE: If FIRE warning annunciator goes OUT, and no other indications of fire are
present, land as soon as practical.
If FIRE warning annunciator remains ON, proceed with next steps.
Engine control switch
OFF FOR AFFECTED ENGINE
Fuel boost pump
OFF FOR AFFECTED ENGINE
Fuel shutoff valve
OFF FOR AFFECTED ENGINE
Fire bottle discharge switch (if installed)
PRI (ALT IF NECESSARY)
NOTE: The fire bottle will not discharge with the fuel valve ON.
Land Immediately
NOTE: If the engine fire extinguishing subsystem is installed, and the FIRE warning light
is extinguished after discharge, land as soon as possible.
Engine control switch
OFF FOR OPERATING ENGINE
Rotor brake (if installed)
APPLY
Power switch
OFF
Passengers/crew
EVACUATE
TRANSMISSION AREA FIRE
Indications: Transmission FIRE warning annunciator ON and activation of the warning
tone for two cycles.
Land immediately
After landing:
Engine control switches
OFF
Rotor brake (if installed)
APPLY
Power switch
OFF
Passengers/crew
EVACUATE
Fire extinguisher
USE AS APPROPRIATE
FAA Approved
Reissue 3
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3−17
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
3−9.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FLIGHT CONTROL MALFUNCTIONS
ANTI-TORQUE FAILURE - GENERAL
Different types of failure require different techniques for optimum success in
recovery. It is not possible to identify all failure scenarios. However, under­
standing the following general guidelines will assist the pilot in controlling the
aircraft.
Pilots facing an anti-torque system malfunction are presented with variables in
types of failure as well as the operating environment at the moment of failure. There­
fore, it is important that the pilot fully understand the effects and use of the remain­
ing functional controls on establishing aircraft directional control.
Anti-torque malfunctions can be caused by jammed or broken thruster cone control
cable (fixed rotating cone), jammed fan linkage (fixed fan thrust), or total failure
of the NOTAR fan (complete loss of thrust).
Upon encountering an anti-torque system malfunction, the following general infor­
mation may be applied by the pilot, when appropriate, to maintain directional control
of the aircraft.
3−18
Evaluate the extent of the condition by (1) applying pedal inputs to determine
the effect (if any) on aircraft yaw and (2) by reducing airspeed and noting
which direction the aircraft tends to yaw. If a pilot determines that a fixed
rotating cone condition exists, the pilot should place the pedals in a “neutral”
position (approximately one inch, [25mm] of right pedal). This “neutral” position
places the NOTAR fan at minimum pitch. Using pedal input in an attempt
to counter the yaw will produce an unfavorable thrust vector, increasing the
yaw.
Normally, the nose of the aircraft should turn right when power (collective)
is increased. Conversely, the nose of the aircraft should turn left when power
(collective) is reduced. The VSCS system will attempt to maintain “trimmed”
flight within its limited authority. When the collective is raised, the vertical
fins reposition to move the aircraft nose to the left. When the collective is
lowered, the vertical fins reposition to move the aircraft nose to the right,
assuming there is sufficient airflow (i.e., airspeed) across the vertical stabiliz­
ers.
The effects of the VSCS can be neutralized by turning both VSCS switches
OFF. This action should only be accomplished with the aircraft established
on final approach and below 100 knots. This procedure is most helpful when
faced with a complete loss of thrust or with a fixed thruster - right pedal
applied condition.
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
Wind speed and direction at the landing site can be beneficial if optimized
for the particular type of anti-torque malfunction. Head winds reduce ground
speed and/or power required at touchdown. Left crosswind components can
help weathervane the aircraft against the yaw tendency caused by the particu­
lar malfunction.
With a fixed collective position, controlling RPM with the twist grips will change
power (torque) and induce a yaw. If needed, it is recommended that controlling
RPM with twist grips be used only to reduce RPM just prior to or at the moment
of touchdown.
NOTE: This action will place both engines in the manual mode.
ANTI-TORQUE FAILURE - COMPLETE LOSS OF THRUST
This involves a break in the fan drive system (e.g., a broken drive shaft) that causes
the fan to stop turning resulting in a complete loss of fan thrust. Directional control
becomes dependent on airspeed and power setting.
Conditions: While in hovering flight
Indications: Inability to “trim” helicopter with pedals; may also be accompanied by
noise or vibration.
Procedures:
If altitude permits, a positive reduction of collective pitch may result in a
stopping or slowing of the “uncommanded turn to the right”.
If “uncommanded turn to the right” is arrested, fly away and gain sufficient
airspeed to maintain heading control.
Proceed with procedures for complete loss of thrust in forward flight.
If unable to gain airspeed or altitude does not permit, reduce power and
altitude with collective.
As the ground is approached, rotate both twist grips simultaneously to IDLE
and perform an autorotation.
FAA Approved
Reissue 3
Original
3−19
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Conditions: In Forward Flight
Indications: Inability to “trim” helicopter with pedals; may also be accompanied by
noise or vibration.
Procedures:
Adjust airspeed and power for level flight at an airspeed between 80 and
100 KIAS.
CAUTION
Do not attempt an autorotation from forward flight unless an actual
dual engine failure occurs.
Select an approach direction that offers a left quartering headwind to reduce
the touchdown ground speed and the amount of right yaw.
Perform a shallow approach to a hard surface or other suitable area at a mini­
mum airspeed of 80 knots.
Set collective friction to 5 pounds.
Turn VSCS OFF.
An aggressive reduction in power (similar to a “quick stop”) as the air­
craft is decelerated prior to landing should yaw the aircraft to the left.
As the ground is approached, level the aircraft and adjust collective as
necessary to align the aircraft with the touchdown direction and cushion
the landing. Landing speed should be as slow as possible, not to exceed
30 knots.
If necessary, just prior to or at the moment of touchdown, rotate both twist
grips simultaneously toward IDLE to assist in maintaining directional control.
NOTE: This action will place both engines in the manual mode.
3−20
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ANTI-TORQUE FAILURE - FIXED THRUSTER SETTING
Conditions: Right pedal applied: This condition results in a thruster opening on the right
and may be understood either as a “stuck right pedal” or a break in the rotating
cone controls with the right pedal applied. In either failure mode, the thruster
would be opened on the right producing a thrust vector that causes the aircraft
to yaw to the right. The degree of yaw will be determined by the position of
the rotating cone at the time of failure.
Procedures:
Adjust airspeed and power for level flight at an airspeed between 80 and
100 KIAS.
CAUTION
Do not attempt an autorotation from forward flight unless an actual
dual engine failure occurs.
If able, place pedals in “neutral” position (approximately one inch [25mm]
of right pedal).
NOTE: With pedals in neutral, the NOTAR fan will be at minimum pitch.
Select an approach direction that offers a left quartering headwind to reduce
the touchdown ground speed and the amount of right yaw.
Perform a shallow approach to a hard surface or other suitable area at a mini­
mum airspeed of 80 knots.
Select collective friction to 5 pounds.
Turn VSCS OFF.
An aggressive reduction in power (similar to a “quick stop”) as the air­
craft is decelerated prior to landing should yaw the aircraft to the left.
As the ground is approached, level the aircraft and adjust collective as
necessary to align the aircraft with the touchdown direction and cushion
the landing. Landing speed should be as slow as possible, not to exceed
30 knots.
If necessary, just prior to or at the moment of touchdown, rotate both twist
grips simultaneously toward IDLE to assist in maintaining directional control.
NOTE: This action will place both engines in the manual mode.
FAA Approved
Reissue 3
Original
3−21
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Conditions: Left pedal applied: This condition results in a thruster opening on the left
and may be understood either as a “stuck left pedal” or a break in the rotating
cone controls with the left pedal applied. In either failure mode, the thruster
would be opened on the left producing a thrust vector that causes the aircraft
to yaw to the left. The degree of yaw will be determined by the position of
the rotating cone at the time of failure.
Procedures:
Adjust airspeed and power for level flight at an airspeed between 80 and
100 KIAS.
CAUTION
Do not attempt an autorotation from forward flight unless an actual
dual engine failure occurs.
If able, place pedals in “neutral” position (approximately one inch, [25mm]
of right pedal).
NOTE: With pedals in neutral, the NOTAR fan will be at minimum pitch.
3−22
Select collective friction to 5 pounds.
VSCS OFF.
Use a shallow to normal approach into wind or left quartering headwind.
Maintain directional control with small adjustments in collective.
Plan to touchdown with little or no forward speed.
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
VSCS FAILURE
LEFT VERTICAL STABILIZER
POSITION INDICATOR
FIN TRAILING EDGE
DEFLECTION INDICATORS
MID-RANGE DEFLECTION
POINT
L
VERTICAL STAB
R
L
VERTICAL STAB
R
RIGHT VERTICAL STABILIZER
POSITION INDICATOR
F90−090
Figure 3−3. VSCS Indicator
Indications: VSCS Fail message(s) on IIDS alpha-numeric display.
VSCS indicator: Abnormal indication - no movement or continuous full-scale
deflection.
Possible uncommanded sideslip in forward flight.
Procedures:
Trim aircraft with pedals.
OFF ON AFFECTED SYSTEM(S)
VSCS
Reduce airspeed below 100 KIAS (Ref. Section II).
Continue flight to next point of intended landing.
FAA Approved
Reissue 3
Original
3−23
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
HYDRAULIC SYSTEM FAILURE
Indications: Single system failure: The `‘1HYD’’ or ‘‘HYD2'' caution annunciator illuminated
on the caution/warning advisory display. Both hydraulic system pressures or
``TEMPERATURE'' indication will be displayed on the IIDS alphanumeric
display. A stiffness in the anti-torque pedals will occur with a failure of the
number 2 system.
Dual system failure: The ``1HYD2'' caution annunciator illuminated on the
caution/warning advisory display. Both hydraulic system pressures or
``TEMPERATURE'' indications will be displayed on the IIDS alphanumeric
display.
Conditions: Single system failure - loss of pressure
Procedures:
Decrease air speed to below 100 KIAS.
NOTE: A stiffness in the anti−torque pedals will occur with a failure of the number 2
system.
Continue the flight to the point of next intended landing.
Perform a shallow approach to a hover; land vertically for a single system
failure.
Conditions: Dual system failure - loss of pressure
Procedures:
Decrease air speed to below 100 KIAS.
Continue the flight to the point of next intended landing.
Perform a running landing.
Conditions: High hydraulic fluid temperature
Procedures:
Land as soon as practical.
CYCLIC TRIM FAILURE
Indications: Cyclic trim failure is indicated by an inability to reduce cyclic forces with the
cyclic trim switch. Cyclic stick forces of approximately 15 pounds may be
required for full control movement.
Procedures:
3−24
Continue flight
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
COLLECTIVE FRICTION FAILURE
Conditions: Collective friction release failure
Indications: 25 lbs of force required to move the collective up or down.
Procedures:
Set collective friction release switch to 5 lb position in an attempt to reduce
control forces.
Continue flight.
Advise maintenance.
Conditions: Collective friction fails to engage
Continue flight.
Indications: Collective control movements will require only 5 lbs of force.
Procedures:
Continue flight, advise maintenance.
3−10. PITOT/STATIC SYSTEM MALFUNCTION: SINGLE OR DUAL PITOT
TUBE INSTALLATION
STATIC SYSTEM MALFUNCTION
Indications: Altimeter and IVSI (if installed) show no change in indication during
climb/descent.
Conditions: Primary static source is clogged.
Procedures:
Alternate static source toggle valve (on
affected side)
PULL UP
NOTE: The altimeter will indicate 60 feet less during climb operations.
SINGLE PITOT TUBE ALTERNATE STATIC SOURCE TOGGLE VALVE
SHOWN; DUAL PITOT TUBE INSTALLATION HAS AN ADDITIONAL
ALTERNATE STATIC SOURCE TOGGLE VALVE LOCATED ON
OPPOSITE SIDE OF INSTRUMENT PANEL
NOTE: TO OPERATE TOGGLE VALVE, PULL VALVE
HANDLE UP. TO RETURN TO PRIMARY STATIC SOURCE,
PUSH HANDLE DOWN
F90−096A
Figure 3−4. Alternate Static Source Toggle Valve
FAA Approved
Reissue 3
Original
3−25
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−11. ENGINE AND GENERATOR MALFUNCTION INDICATIONS
NOTE: Certain malfunctions may require an engine to be shutdown, however, the pilot
must assess the type of problem and decide if the affected engine is to remain
operational.
ENGINE CHIPS CAUTION
ANNUNCIATOR (YELLOW)
ENGINE FIRE WARNING
ANNUNCIATOR (RED)
HIGH ENGINE OIL TEMPERATURE
WARNING ANNUNCIATOR (RED)
CAUTION ANNUNCIATOR
(YELLOW)
FIRE
CHIPS
ENGINE LOW OIL TEMPERATURE
CAUTION ANNUNCIATOR (YELLOW)
GENERATOR HIGH LOAD
CAUTION ANNUNCIATOR (YELLOW)
° C %PSI
LOW ENGINE OIL PRESSURE
CAUTION ANNUNCIATOR (YELLOW)
WARNING ANNUNCIATOR (RED)
%LOAD
GEN
NG HIGH
WARNING ANNUNCIATOR (RED)
NG HIGH
CAUTION ANNUNCIATOR (YELLOW)
GENERATOR LOAD
DIGITAL DISPLAY (WHITE)
NG
GENERATOR OUT CAUTION
ANNUNCIATOR (YELLOW)
HIGH ENGINE OIL PRESSURE
CAUTION ANNUNCIATOR (YELLOW)
NG LOW WARNING
ANNUNCIATOR (RED)
F90−026
Figure 3−5. Engine and Generator Malfunction Annunciators
ENGINE HIGH OIL TEMPERATURE
Indications: Upper yellow caution annunciator ON at 105°C and/or red warning annunciator
ON at 110°C
NOTE: The engine is certified to operate continuously up to 110°C. The caution range
and yellow annunciator are advisories only and indicate temperatures
approching maximum.
Procedures:
Reduce power on affected engine.
Monitor pressure and temperature.
NOTE: If temperature remains above limits (red annunciator ON) and/or abnormal oil
pressure is indicated, shut down affected engine.
3−26
If indications return to normal, increase power on affected engine as desired.
Land as soon as practical.
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ENGINE LOW OIL TEMPERATURE
Indications: Lower yellow caution annunciator ON at +10°C and below
Procedures:
Allow engine oil temperature to increase to normal range before placing Engine
Control in FLY.
ENGINE HIGH OIL PRESSURE
NOTE: The red high engine oil pressure annunciator is only activated during the lamp
test mode.
Indications: Upper yellow caution annunciator ON if the oil pressure is greater than 112%
psi for more than 10 minutes.
Procedures:
Land as soon as practical.
ENGINE LOW OIL PRESSURE
Indications: Lower yellow caution annunciator or lower red warning annunciator ON.
Procedures:
If single engine power is sufficient to continue flight, shut down affected engine.
FAA Approved
Reissue 3
Original
3−27
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENGINE CHIPS
Indications: Yellow CHIPS caution annunciator ON.
Conditions: On ground:
Shut down engine.
Conditions: In flight:
Land as soon as practical.
NG HIGH
Indications: Red warning or yellow caution annunciator ON.
Procedures:
Reduce power to normal range
Check engine torque and EGT indications
NG LOW
Indications: Red warning annunciator ON.
Procedures:
3−28
Check affected engine IIDS indications (primary display) for possible engine
failure.
If engine failure is confirmed, proceed with engine failure procedures (Ref.
paragraph 3-3).
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
GENERATOR HIGH LOAD
Indications: Upper yellow generator high load annunciator ON
Procedures:
Turn off unnecessary electrical equipment.
CAUTION
Failure to turn off unnecessary electrical equipment may cause
the generator(s) to automatically go off line.
GENERATOR
Indications: Yellow GEN annunciator ON and %LOAD is ``0''.
Procedures:
L GEN or R GEN (or both if dual generator
failure) switch
RESET
If GEN annunciator still on
OFF FOR AFFECTED
GENERATOR(S)
Continue flight
If both generators failed and both fuel boost pumps are indicating low fuel
pressure:
Power switch
Land as soon as possible; avoid high ``G'' maneuvers.
If both generators failed and both fuel boost pumps are indicating normal
fuel pressure:
reduce electrical load to minimum required
Land as soon as practical.
ESNTL UNLESS FLIGHT
CONDITIONS DICTATE
OTHERWISE
NOTE: With both generators failed and the power switch in the ESNTL position, a fully
charged battery will supply power for up to one hour..
WIth the power switch in the ESNTL position, only that equipment powered by
the essential bus will be operational.
FAA Approved
Reissue 3
Original
3−29
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−12. TRANSMISSION MALFUNCTION INDICATIONS
TRANSMISSION
HIGH OIL TEMP WARNING
ANNUNCIATOR (RED)
TRANSMISSION
HIGH OIL TEMP CAUTION
ANNUNCIATOR (YELLOW)
TRANSMISSION
LOW OIL TEMP
CAUTION
ANNUNCIATOR
(YELLOW)
FIRE WARNING
ANNUNCIATOR (RED)
TRANSMISSION CHIPS CAUTION
ANNUNCIATOR (YELLOW)
TRANSMISSION
HIGH OIL PRESSURE
WARNING ANNUNCIATOR (RED)
FIRE
CHIPS
TRANSMISSION
HIGH OIL PRESSURE CAUTION
ANNUNCIATOR (YELLOW)
° C %PSI
TRANSMISSION
LOW OIL PRESSURE CAUTION
ANNUNCIATOR (YELLOW)
TRANSMISSION
LOW OIL PRESSURE
WARNING
ANNUNCIATOR (RED)
F90−023
Figure 3−6. Transmission Malfunction Annunciators
TRANSMISSION OIL TEMPERATURE HIGH
Indications: Upper yellow caution or red annunciator ON.
Procedures:
3−30
Reduce power
If temperature remains high
FAA Approved
Reissue 3
Original
LAND AS SOON AS POSSIBLE
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
TRANSMISSION OIL TEMPERATURE LOW
Indications: Lower yellow caution annunciator ON.
Procedures:
Continue flight
Do not takeoff with low temperature annunciator ON.
TRANSMISSION OIL PRESSURE LOW
Indications: Lower yellow caution annunciator ON or red warning annunciator ON.
Procedures:
Transmission oil pressure low caution
LAND AS SOON AS
POSSIBLE
Transmission oil pressure low warning
LAND IMMEDIATELY
TRANSMISSION OIL PRESSURE HIGH
Indications: Upper yellow caution annunciator ON or red warning annunciator ON.
Procedures:
Monitor transmission oil pressure
Land as soon as practical
TRANSMISSION CHIPS
Indications: Yellow CHIPS annunciator ON.
Procedures:
Monitor transmission oil temperature and pressure. If normal, land as soon
as practical.
If temperature/pressure are not normal, land as soon as possible.
FAA Approved
Reissue 3
Original
3−31
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−13. FUEL SYSTEM DISPLAY ADVISORIES
FIRE
FIRE
FIRE
CHIPS
CHIPS
CHIPS
CAB HEAT
BAT HOT
BAT WRM
°C %PSI
°C %PSI
°C %PSI
FUEL
%LOAD
GEN
%LOAD
GEN
NG
ROTOR
BRAKE
CABIN
DOOR
BAGGAGE
DOOR
1 HYD 2
IIDS
FUEL FILTER
IMPENDING
BY-PASS CAUTION
(YELLOW)
(NOTE 1 )
CROSSFEED VALVE
POSITION (WHITE)
FUEL SHUTOFF
VALVE (YELLOW)
(NOTE 1)
FUEL FILTER
IMPENDING BY-PASS
CAUTION
FUEL SHUTOFF
VALVE (YELLOW)
(NOTE 1)
NG
°C
OAT
LB
ÇÇ
ÂÂ
ÉÉ
ÂÂ
YELLOW
WHITE
RED
GREEN
A. NORMAL FUEL PRESSURE WITH CROSSFEED VALVE SHOWN IN
NORMAL CLOSED POSITION ON IIDS SECONDARY DISPLAY PANEL
B. NORMAL FUEL PRESSURE WITH CROSSFEED VALVE OPEN (NOTE 1)
C. NORMAL FUEL FLOW WITH IMPENDING ENGINE FUEL FILTERS BY-PASS
ÉÉÉÉ
ÉÉÉÉ
ÉÉÉÉ
ÉÉÉÉ
ÉÉÉÉ
ÇÇÇÇ
ÉÉÇÇÇÇ
ÉÉÉÉÉ
ÈÈÈÈ
ÍÍÍÍ
FUEL
LOW FUEL
WARNING
TICK (RED)
LB
D. INDICATES LOW FUEL PRESSURE ON BOTH FUEL BOOSTER PUMPS
OR BOTH BOOSTER PUMPS IN OFF POSITION
FUEL QUANTITY
SEGMENTS
LOW FUEL CAUTION
SEGMENT
(YELLOW)
E. LOW FUEL PRESSURE LEFT BOOSTER PUMP WITH NORMAL FUEL
PRESSURE ON RIGHT BOOSTER PUMP
LOW FUEL WARNING SEGMENT
(RED)
F. INDICATES BOTH FUEL SHUTOFF VALVES IN CLOSED POSITION (NOTE 1)
FUEL QUANTITY DIGITAL
DISPLAY (WHITE)
NOTE:
1. THE LIGHT SEGMENT BAR(S) WILL FLASH ON THE IIDS PANEL WHEN
THE VALVE IS IN TRANSIT BETWEEN THE OPEN AND CLOSED POSITION.
F90−089
Figure 3−7. Fuel System Advisory Indicators
3−32
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
FUEL LOW
Indications: Fuel quantity displays yellow caution bars when fuel level decreases to 300
pounds; the red warning bar displays at 150 pounds. Low fuel warning tick
marks display at 97 to 117 LBS.
NOTE: 100 lbs of fuel equals approximately 12 minutes of fuel in cruise flight at sea level,
standard day conditions, 6000 lbs gross weight (Ref. Section IX).
Procedures:
With low fuel warning tick marks ON
140 KIAS MAXIMUM AND AVOID
UNCOORDINATED
TURNS/MANEUVERS
FUEL BOOST PUMP FAILURE
Indications: Alternating white and yellow offset segments indicate low fuel pressure.
Procedures: Single Failure
Crossfeed ON to provide pressurized fuel to opposite side.
Continue flight.
Procedures: Dual Failure
Land as soon as possible. Avoid high ``G'' maneuvers.
CROSSFEED VALVE MALFUNCTION
Indications: With Crossfeed ON, crossfeed indicator will not appear or will not appear steady.
Procedures:
With single fuel boost pump failure
LAND AS SOON AS
PRACTICAL − AVOID HIGH ‘G’
MANEUVERS
NOTE: With a Crossfeed Valve malfunction and operating OEI, the unusable fuel
quantity increases approximately 10 pounds.
FAA Approved
Reissue 3
Original
3−33
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SINGLE FUEL PROBE FAILURE
Indications: Digital fuel quantity indicator blanked
Vertical fuel quantity segments indicate approximately half the remaining fuel
quantity.
Procedures:
Continue the flight using consumption and time calculations.
DUAL FUEL PROBE FAILURE
Indications: Digital fuel quantity indicator blanked.
Vertical quantity segments blanked.
Procedures:
Continue the flight using consumption and time calculations.
NOTE: The low fuel warning tick mark indication remains operational with a dual fuel
probe failure.
IMPENDING FUEL FILTER BYPASS
Indications: Impending bypass is shown by an inverted ``U''
above affected fuel flow line.
Procedures:
3−34
Continue flight
If other bypass indicator is displayed
FAA Approved
Reissue 3
Original
LAND AS SOON AS
POSSIBLE
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
FUEL SHUTOFF VALVE MALFUNCTION
Indications: Two yellow bar segments flashing above and below the fuel flow line to the
left or right of center.
Conditions: Fuel valve not fully opened/closed
Procedures:
In flight:
Continue flight
Be prepared for affected engine to flame out
Pre Start:
Fuel shutoff switch
CYCLE OFF TO ON
If no change in indication
DO NOT ATTEMPT START
3−14. CAUTION AND WARNING ADVISORIES
CAB HEAT
BAT HOT
BAT WRM
ROTOR
BRAKE
CABIN
DOOR
BAGGAGE
DOOR
1 HYD 2
IIDS
°C
OAT
CABIN HEAT
WARNING ANNUNCIATOR (RED)
BATTERY HOT
WARNING ANNUNCIATOR (RED)
BATTERY WARM
CAUTION ANNUNCIATOR (YELLOW)
ROTOR BRAKE
CAUTION ANNUNCIATOR (YELLOW)
CABIN DOOR OPEN
CAUTION ANNUNCIATOR (YELLOW)
BAGGAGE DOOR OPEN
CAUTION ANNUNCIATOR (YELLOW)
HYDRAULIC SYSTEM
PRESSURE OR HIGH TEMPERATURE
CAUTION ANNUNCIATOR (YELLOW)
IIDS MALFUNCTION
CAUTION ANNUNCIATOR (YELLOW)
F90−024B
Figure 3−8. Caution/Warning Cluster
FAA Approved
Reissue 3
Original
3−35
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CABIN HEAT
Indications: Red cab heat annunciator ON and activation of the warning tone for two seconds.
Conditions: Bleed air leak
Procedures:
Turn CAB HEAT switch OFF.
BATTERY HOT
Indications: Red BAT HOT warning annunciator ON (battery internal temperature 71°C)
and activation of the warning tone for two cycles.
Conditions: On ground
Procedures:
Shut down aircraft.
Service or replace battery prior to next flight.
WARNING
Overheated battery can cause burns to personnel unless
protective clothing and adequate tools are utilized. In some
instances the battery may cause a secondary fire or may rupture
adding the further danger of electrolyte burns. Exercise caution
in dealing with an overheated battery. Maintain extinguisher ready
for use. Do no use the fire extinguisher to cool the battery.
Conditions: In flight
Procedures:
3−36
Power switch OFF.
Land as soon as possible
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
BATTERY WARM
Indications: Yellow BAT WRM annunciator ON (battery internal temperature 57°C).
Conditions: On ground
CAUTION
Do not attempt to start an engine on battery power with BAT WRM
annunciatorON.
NOTE: A battery warm condition results in the battery being disconnected from the
aircraft electrical system once a generator is placed on line. Generator power
alone is not sufficient to start an engine.
Procedures:
Utilize a GPU to start engines.
Power switch OFF after both generators are on line.
If battery warm annunciator remains ON for more than five minutes, shutdown
the aircraft.
Otherwise, continue flight.
Service or replace battery prior to next flight.
Conditions: In flight
Procedures:
Power switch off.
Continue flight.
Service or replace battery prior to next flight.
FAA Approved
Reissue 3
Original
3−37
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ROTOR BRAKE
Indications: Yellow ROTOR BRAKE annunciatorON.
Procedures:
CHECK STOWED
Rotor brake handle
If annunciator remains on, land as soon as possible.
BAGGAGE DOOR
Indications: Yellow BAGGAGE DOOR annunciator ON.
Conditions: On ground
Procedures:
Secure door.
Conditions: In the air
Procedures:
Land as soon as practical and secure the door.
IIDS
Indications: Yellow IIDS annunciator ON.
Conditions: IIDS fault
Procedures:
3−38
Continue flight.
Check fault log after landing; advise maintenance.
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
3−15. OTHER MALFUNCTION/ADVISORIES
IIDS FAILURE
Indications: IIDS displays blanks.
Conditions: Loss of electrical power to IIDS.
Procedures: On ground
Shut down.
Procedures: In flight
Reduce airspeed to 100 KIAS or less.
Reduce electrical load.
Land as soon as practical.
NP SWITCH FAILURE
Indications:
NP switch inoperative.
Procedures: At 100%NP
Continue flight. When arriving at destination, avoid right quartering tailwinds.
Procedures: At 104%NP
Restrict airspeed to 100 KIAS maximum.
Continue flight.
IPS BYPASS
Indications: IPS BYPASS message on IIDS alphanumeric display.
Conditions: Both IPS bypass doors open.
Procedures: Advisory only
BATTERY DISCHARGE
Indications: BATT DISCHARGE message on IIDS alphanumeric display.
Conditions: Battery bus voltage is less than 26 volts
Procedures:
Check generator load indications.
Recycle GEN switches as required.
FAA Approved
Reissue 3
Original
3−39
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
3−16. VIBRATIONS
Indications: Sudden, unusual or excessive vibrations occurring during flight.
Conditions: The onset of unusual or excessive vibrations in the helicopter may be an
indication of problems in the rotor or drive train systems.
Procedures:
LAND AS SOON AS POSSIBLE.
No further flights should be attempted until the cause of the vibration
has been identified and corrected.
Indications: “CHECK NOTAR BAL” or “CHECK ROTOR BAL” on IIDS alphaneumeric
display.
Conditions: NOTAR fan or main rotor balance out of acceptable range.
Procedures:
Clear message from adphaneumeric display.
Land as soon as practical.
If the message on alphaneumeric display reappears during the
CAUTION same flight, land as soon as possible.
Advise maintenance.
3−17. EMERGENCY EQUIPMENT
Emergency Fire Extinguisher:
The fire extinguisher mounts to the aft side of the center console. It detaches
from the mounting bracket by unfastening the quick release clamps. The extin­
guisher uses Halon 1211 extinguishing agent. The fire extinguisher is equipped
with a pressure gauge that indicates normal, charge, and overcharge pressures.
9G26-017
Figure 3−9. Emergency Fire Extinguisher
First Aid Kit:
The first aid kit is located on the right hand sidewall panel of the baggage compart­
ment.
3−40
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
3−18. EMERGENCY EGRESS
Crew compartment doors:
Both doors function as primary and emergency exits.
Cabin door window removal:
Each cabin door window may be used as an emergency exit by pulling the emergency
exit pull tab and pulling the window inward.
RIGHT SHOWN
LEFT OPPOSITE
COCKPIT DOOR FRAME
LOOKING OUTBOARD
RIGHT SIDE
1. LOCATED ON UPPER
COCKPIT DOOR FRAME
2. LOCATED ADJACENT
CREW COMPARTMENT DOOR EXIT
TO COCKPIT DOOR
ACCESS HANDLE
EMERGENCY EXIT RELEASE
EMERGENCY EXIT
PULL TAB
TO REMOVE WINDOW
CABIN DOOR EMERGENCY EXIT
F90−091A
Figure 3−10. Cabin Door Emergency Exit
FAA Approved
Reissue 3
Original
3−41
CSP−900RFM206A−1
Emergency and
Malfunction Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
3−42
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
SECTION IV
NORMAL PROCEDURES
TABLE OF CONTENTS
PARAGRAPH
PAGE
4-1. Preflight Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-1
Figure 4-1. Pilot's Preflight Guide (Sheet 1 of 2 Sheets) . . . . . . . . . . . . . . . . . . .
4-2
Figure 4-1. Pilot's Preflight Guide (Sheet 2 of 2 Sheets) . . . . . . . . . . . . . . . . . . . .
4-3
4-2. Pilot's Daily Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-4
4-3. Pilot's Preflight Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-2. Instrument Panel - Single Pilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-3. Instrument Panel - Two Pilot . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-4. Switches and Circuit Breakers - Console Mounted (Typical) . . . .
Figure 4-5. Circuit Breakers - Baggage Compartment Mounted (Typical) . . .
Figure 4-6. Collective Pitch Stick Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-7. Cyclic Stick Grip . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-15
4-16
4-17
4-18
4-19
4-20
4-21
4-4. Engine Pre-Start Cockpit Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-22
4-5. Engine Starting - Automatic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-24
4-6. Engine Runup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-25
4-7. Before Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-25
4-8. Takeoff . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-26
4-9. Cruise . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-26
4-10. Slow Flight/Approach . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-26
4-11. Landing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-8. Tail Skid to Landing Surface Clearance . . . . . . . . . . . . . . . . . . . . . . .
4-27
4-27
4-12. Engine/Aircraft Shutdown - Normal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-9. Cyclic Centering . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-28
4-30
4-13. Post Flight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-30
4-14. Noise Impact Reduction Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-31
4-15. Flight With Doors Removed or Cabin Doors Open . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 4-10. Cabin Door Hold Open Device . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-32
4-32
4-16. One Engine Inoperative Training . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-33
4-17. Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
4-33
FAA Approved
Reissue 3
Original
4−i
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
4−ii
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
SECTION IV
NORMAL PROCEDURES
4−1.
PREFLIGHT REQUIREMENTS
NOTE: The checks described in this Section apply to the standard configuration MD900
and do not include certain optional equipment items. Preflight checks for optional
equipment items may be found in Section X of this manual. If your helicopter is
equipped with STC’d items, refer to the STC holder’s flight manual supplement.
``CHECK'' means to observe the helicopter and note any obvious damage. Damage
is defined as any condition that is not normal or not within limits. Examples of
conditions to look for are: inoperable equipment, excessive leakage, discoloration
caused by heat, loose attachment, dents, cracks, punctures, abrasion, chafing, gall­
ing, nicks, scratches, delamination and evidence of corrosion. These are the most
common types of damage, however, checks should not be limited to these items.
Further checks shall be performed before the next flight if discrepancies are noted
to determine if the aircraft is airworthy. Flight is prohibited when unrepaired damage
exists which makes the aircraft unairworthy.
Have a thorough understanding of operating limitations. (Ref. Section II).
Service helicopter as required. (Ref. Section VIII and the Aircraft Maintenance
Manual).
Determine that helicopter loading is within limits. (Ref. Sections II and VI).
Check helicopter performance data. (Ref. Sections V, IX, and X).
CAUTION
Be sure to include a review of the appropriate flight manual
supplemental data for type of optional equipment installed
(including STC items) as a regular part of preflight planning.
Perform Pilot's Daily Preflight check prior to the first flight of the day.
Perform Pilot's Preflight Check prior to subsequent flights that same day.
Brief passengers on relevant operational procedures and associated hazards (Ref.
Section I).
FAA Approved
Reissue 3
Original
4−1
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
F
Figure 4−1. Pilot’s Preflight Guide (Sheet 1 of 2 Sheets)
4−2
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
F90−027−2A
Figure 4−1. Pilot’s Preflight Guide (Sheet 2 of 2 Sheets)
FAA Approved
Reissue 3
Original
4−3
CSP−900RFM206A−1
Normal Procedures
4−2.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PILOT’S DAILY PREFLIGHT CHECK
Perform these checks prior to the first flight of the day.
PRELIMINARY CHECKS
Aircraft attitude
CHECK
Covers and tiedowns
REMOVE
Main rotor blades
CHECK
EXTERIOR CHECKS − FRONT
Battery compartment
BATTERY CONNECTED; SECURE
Battery compartment door
CONDITION; CLOSED
Pitot tube(s)
CONDITION, FREE OF
OBSTRUCTIONS
Windscreen
CONDITION
Chin windscreen
CONDITION
CHECK PEDAL LINKAGES;
FOREIGN OBJECTS
Landing light window and lights
Fuselage Bottom:
Antennas
CHECK
OAT probe
CHECK
Chin windscreen area
CONDITION
FORWARD RIGHT SIDE
Right crew door:
4−4
Glass and vents
Hinges
Latch system and handle
Door release handle
SECURITY, CONDITION
CHECK
CHECK OPERATION
CONDITION
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
OPERATION, SECURITY, CONDITION
CONDITION; NOTHING STOWED
UNDER SEAT
Door strut and strap
Crew Seat
Pilot pedals:
Adjust
ADJUSTMENT PINS ENGAGED
OBSERVE MOVEMENT OF THRUSTER
Move pedals by hand
Electrical master panel:
POWER switch
IIDS panel:
Fuel quantity
BAT/EXT
CHECK LAMP TEST MODE (B.I.T.)
CHECK
NOTE: If the Range Extender is installed the fuel quantity indication will not display
actual fuel weight when the fuel system is ‘‘topped off’’. Remove fuel cap and pull
lanyard to assure tank is full by noting fuel level on the inside of filler neck (Ref.
Section VIII). Fuel can be trapped in filler neck by the flapper valve.
CHECK OPERATION OF LIGHTS AS
REQUIRED
Lighting control panel
Electrical master panel:
POWER switch
Crew door
OFF
CLOSE
FUSELAGE − RIGHT SIDE
Landing gear:
Skid tube step
SECURITY, CONDITION
Forward spacer fitting; crosstube
CHECK
Skid tube and abrasion strips
CHECK
Aft crosstube and damper fluid level
CHECK (REF. SECTION VII)
Aft fuel vent fairing
CLEAR OF OBSTRUCTIONS
Fuel catch can drain (if installed)
DRAIN
Fuel sump drain:
Push in fuel drain control to take sample CHECK FOR CONTAMINATION;
VERIFY PROPER OPERATION OF
DRAIN VALVES
Fuel drain door
Forward fuselage skin and steps
CLOSED
CONDITION
FAA Approved
Reissue 3
Original
4−5
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Auxiliary power door, avionics access panel, SECURITY, CONDITION
static port, fuel cap
Right side passenger door:
Upper and lower track and guide
CHECK
Door rollers
CHECK OPERATION
Door skin and glass
CHECK
Door stops/pins
CHECK
Right side passenger compartment:
Upholstery
CHECK CONDITION
Seats and seat belts
CHECK OPERATION
Cabin heat controls
AS DESIRED
Loose equipment
STOWED
NOTE: Nothing stowed under seats that are to be occupied.
RIGHT FORWARD TRANSMISSION DECK
Hydraulic System:
Hydraulic manifold
CHECK MOUNTING AND FLUID LEVEL
System filters
CHECK IMPENDING BYPASS
INDICATORS (REF. SECTION VIII)
Longitudinal hydraulic actuator
CHECK LEAKS, MOUNTING
Hydraulic lines
CHECK LEAKS, FITTINGS
Static mast supports
CHECK ATTACHMENT
Rotor brake fluid level
CHECK (IF INSTALLED)
Environmental control system:
Air inlet screen
CHECK
Cabin air and fan plenum
CHECK MOUNTING
Air ductwork
CHECK CONDITION
4−6
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Transmission deck
Oil cooler
Forward access door
CSP−900RFM206A−1
Normal Procedures
CHECK FOR FOREIGN OBJECTS AND
SIGNS OF FLUID LEAKAGE
CHECK LEAKS
CHECK OPERATION AND CONDITION;
CLOSE
RIGHT CENTER TRANSMISSION DECK
Oil cooler:
Cooling air inlet
NO OBSTRUCTIONS
Oil cooler
CHECK MOUNTING AND CONDITION
Air ducts
CHECK MOUNTING AND CONDITION
Transmission:
Transmission oil level
CHECK
Transmission oil filler cap
CHECK SECURITY
Static mast support
CHECK MOUNTING AND CONDITION
Forward outside engine mount
CHECK MOUNTING AND CONDITION
Engine drive shaft
CHECK
Fan drive shaft
CHECK
Rotor brake
CHECK
Transmission deck
CHECK FOR FOREIGN OBJECTS AND
SIGNS OF FLUID LEAKAGE
Engine accessory gear box
CHECK FITTINGS, LINES, CONNECTORS
AND WIRING
Engine oil level
CHECK: IF SIGHT GLASS IS DARK, OIL
LEVEL IS FULL
Engine oil filter
CHECK BYPASS INDICATOR
NOTE: To reduce the possibility of over servicing and ensure accurate readings for oil
consumption measurement, it is recommended that oil level always be checked
within 10 minutes after engine shutdown. If oil level is in doubt, check at filler
dipstick (Ref. Section VIII)
FAA Approved
Reissue 3
Original
4−7
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Transmission access door latches, hinges,
and door
CHECK OPERATION; CLOSE
Cabin door closed and latched
CHECK
FUSELAGE −RIGHT TOP REAR
CHECK
Work platforms/steps.
Engine air inlet w/o particle separator:
Inlet screen
CHECK − NO OBSTRUCTIONS
NACA inlet (if installed)
NO OBSTRUCTIONS
Engine air inlet with particle separator:
Particle separator
CHECK − NO OBSTRUCTIONS
Bypass door
CLOSED; CONDITION OF SEAL
NACA inlet door (if installed)
CLOSED − NO OBSTRUCTIONS
Right Engine:
Engine oil access door
CHECK CONDITION
Engine oil level
CHECK AS NECESSARY
Oil filler cap
CHECK
Engine cowling assembly
CHECK
Fuselage skin
Notar fan inlet:
Fan air inlet screen and duct
CHECK CLEAR
Notar fan blades
CHECK
CHECK CONDITION
ROTOR SYSTEM
Stationary swashplate
CHECK
Lower control rodend bearings
CHECK
Rotating swashplate
CHECK
Scissors drive link
CHECK
Pitch change links
CHECK
4−8
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
Striker plates and rollers
CHECK
Inner flexbeam attach points
CHECK
Flexbeam lead and lag legs
CHECK
Upper and lower damper and damper caps
CHECK
Elastomeric feathering bearing
CHECK
Pitch change housing
CHECK
Blade attach pins (bolts):
Check for upward or downward shift of
installed blade retention bolts.
Check blade retention bolts for gap be­
tween thrust washer and retainer.
Blade attach points
CHECK
ADVISE MAINTENANCE IF SHIFT IS
NOTED
ADVISE MAINTENANCE IF NO GAP IS
PRESENT
CHECK
Rotor blades
CHECK
Top of rotor head
CHECK
FUSELAGE − RIGHT REAR
Fuselage skin
Exhaust ejector cowl
Baggage door:
Handle
Skin
Door strut
Rear spoiler
Hinge pins
Environmental control system vent
Baggage compartment:
Loose items
Circuit breaker panel
Fan Control Rod Spring Capsule:
• Baggage compartment ceiling panel
• •
• • •
Control rod spring capsule
CHECK
CHECK
OPERATION
CHECK
CHECK
CHECK
CHECK
CHECK
SECURED
CHECK
UNZIP
CHECK
NOTE: Check piston rod for movement, clips installed on outer bellcrank assembly and
• • •
lanyards connected to clips. If clips are bent and/or lanyards are taut, or piston
rod moves in any direction, advise maintenance.
Baggage compartment ceiling panel
ZIP UP
Baggage door
CLOSED AND LATCHED
FAA Approved
Reissue 3
Original
4−9
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TAILBOOM AND EMPENNAGE − RIGHT SIDE
Tailboom attach ring
CHECK
Tailboom slots
CLEAR OF OBSTRUCTIONS
Tailboom
CHECK CONDITION
Horizontal stabilizer:
Horizontal stabilizer attach points
CHECK
Horizontal stabilizer fairing
CHECK
Vertical stabilizer
CHECK
Nav light/strobe lenses
CHECK
Thruster rotating cone:
CHECK FOR FREEDOM OF ROTATION
Place hands at the 11 and 5 o'clock positions and press inward while rotating the
cone to the left and right. Repeat check by using the 1 and 7 o'clock positions. Ad­
vise maintenance if any unusual noise or roughness is noticed.
CAUTION: Do not rotate cone beyond one−half left/right open.
CHECK
Turning vanes
TAILBOOM AND EMPENNAGE − LEFT SIDE
Horizontal stabilizer:
Horizontal stabilizer attach points
CHECK
Horizontal stabilizer fairing
CHECK
Tail skid
CHECK
Vertical stabilizer
CHECK
Nav light
CHECK
Tailboom
CHECK CONDITION
Tailboom attach ring
CHECK
4−10
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
LEFT REAR FUSELAGE
Fuselage skin
CHECK
Exhaust ejector cowl
CHECK
Work platforms/steps
CHECK
FUSELAGE − LEFT SIDE
Landing gear:
CHECK
Aft crosstube and damper fluid level
CHECK (REF. SECTION VII)
Passenger step
CHECK
Skid tube and abrasion strips
CHECK
Forward spacer fitting; crosstube
CHECK
Skid tube step
SECURITY, CONDITION
Underside of fuselage:
Fuel catch can drain (if installed)
DRAIN
Fuselage skin
CHECK
Left side passenger door:
Upper and lower track and guide
CHECK
Door rollers
CHECK OPERATION
Door skin and glass
CHECK
Door stops/pins
CHECK
Left side passenger compartment:
Upholstery
CHECK CONDITION
Seats and seat belts
CHECK OPERATION
Loose equipment
STOWED
NOTE: Nothing stowed under seats that are to be occupied.
FAA Approved
Reissue 3
Original
4−11
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FORWARD LEFT SIDE
Left crew/passenger door:
Glass and vents
SECURITY, CONDITION
Hinges
CHECK
Latch system and handle
CHECK OPERATION
Door release handle
CONDITION
Door strut and strap
OPERATION, SECURITY, CONDITION
Crew Seat
CONDITION; NOTHING STOWED
UNDER SEAT
NOTE: Nothing stowed under seats that are to be occupied.
Co-pilot pedals (if installed)
ADJUSTED; ADJUSTMENT PINS
ENGAGED
Crew door
CLOSE
Avionics access panel
CHECK
Static port
CHECK: NO OBSTRUCTIONS
Fwd fuel vent fairing
CHECK: NO OBSTRUCTIONS
LEFT FORWARD TRANSMISSION DECK
Hydraulic System:
Hydraulic manifold
CHECK MOUNTING AND FLUID LEVEL
System filters
CHECK IMPENDING BYPASS
INDICATORS (REF. SECTION VIII)
Lateral and collective hydraulic actua­
tors
CHECK LEAKS, MOUNTING
Hydraulic hand pump (if installed)
CHECK LEAKS, FITTINGS
Hydraulic lines
CHECK LEAKS, FITTINGS
Static mast supports
4−12
CHECK ATTACHMENT
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
Environmental control system: (if installed)
Evaporator
CHECK
Freon lines
CHECK
Air ductwork
CHECK CONDITION
Transmission deck
CHECK FOR FOREIGN OBJECTS AND
SIGNS OF FLUID LEAKAGE
Transmission oil filter
CHECK BYPASS INDICATOR (REF.
SECTION VIII)
Oil cooler
CHECK LEAKS
Forward access door
CHECK OPERATION AND CONDITION;
CLOSE
LEFT CENTER TRANSMISSION DECK
Oil cooler:
Cooling air inlet
NO OBSTRUCTIONS
Oil cooler
CHECK MOUNTING AND
CONDITION
Air ducts
CHECK MOUNTING AND
CONDITION
Static mast support
CHECK MOUNTING AND
CONDITION
Forward outside engine mount
CHECK MOUNTING AND
CONDITION
Engine drive shaft
CHECK
Fan drive shaft
CHECK
Rotor brake
CHECK
Transmission deck
CHECK FOR FOREIGN OBJECTS AND
SIGNS OF FLUID LEAKAGE
Engine accessory gear box
CHECK FITTINGS, LINES,
CONNECTORS AND WIRING
Engine oil level
CHECK: IF SIGHT GLASS IS DARK,
OIL LEVEL IS FULL
FAA Approved
Reissue 3
Original
4−13
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NOTE: To reduce the possibility of over servicing and ensure accurate readings for oil
consumption measurement, it is recommended that oil level always be checked
within 10 minutes after engine shutdown. If oil level is in doubt, check at filler
dipstick (Ref. Section VIII).
Engine oil filter
CHECK BYPASS INDICATOR
Transmission access door latches, hinges,
and door
CHECK OPERATION; CLOSE
Cabin door closed/open and latched/secured CHECK
FUSELAGE − LEFT TOP REAR
Engine air inlet w/o particle separator:
Inlet screen
CHECK − NO OBSTRUCTIONS
NACA inlet (if installed)
NO OBSTRUCTIONS
Engine air inlet with particle separator:
Particle separator
CHECK − NO OBSTRUCTIONS
Bypass door
CLOSED; CONDITION OF SEAL
NACA inlet door (if installed)
CLOSED − NO OBSTRUCTIONS
Left Engine:
Engine oil access door
CHECK
Engine oil level
CHECK AS NECESSARY
Oil filler cap
CHECK
Engine cowling assembly
CHECK
4−14
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
4−3.
CSP−900RFM206A−1
Normal Procedures
PILOT’S PREFLIGHT CHECK
Perform these checks prior subsequent flights of the same day.
Fluid levels
CHECK
Transmission deck - signs of fluid leakage
CHECK
Air inlet screens/particle separators
CHECK
Fuel cap, access doors and panels
CHECK
Rotor blades
CHECK BLADE RETENTION BOLTS
(PINS)
Tailboom and empennage
CHECK
Cargo and loose equipment
CHECK
Baggage, cabin and crew doors
CHECK
FAA Approved
Reissue 3
Original
4−15
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AIRSPEED
INDICATOR
MAGNETIC COMPASS
IIDS
ALTIMETER
NACA DOOR INDICATORS
(IF INSTALLED)
IVSI
VSCS INDICATOR
ALTERNATE STATIC
SOURCE TOGGLE VALVE
FOOT HEATER
CONTROL VALVE
F90−028−1A
Figure 4−2. Instrument Panel − Single Pilot
4−16
FAA Approved
Reissue 3
Original
NOTE 2:
NOTE 2:
ALTERNATE STATIC SOURCE
TOGGLE VALVE FOR LEFT SIDE
PITOT/STATIC INSTRUMENTS
WHEN DUAL PITOT SYSTEM
INSTALLED
F90−028−2B
NOTE 1:
NOTE 1:
ALTERNATE STATIC SOURCE
TOGGLE VALVE
4−17
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Figure 4−3. Instrument Panel − Two Pilot
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENGINE CONTROL
OVSP TEST
R ENGINE
L ENGINE
IDLE FLY TRAIN
IDLE FLY TRAIN
OFF
OFF
UTILITY PANEL
KEY SWITCH
COCKPIT HEAT CONTROL
FUEL SYSTEM
L BOOST
CROSS FEED
R BOOST
ON
ON
ON
HYD
TEST
CAB
HEAT
OFF
OFF
OFF
SYS 1
OVRD
FUEL SHUTOFF
AC/VENT
ON
OFF
IPS
ON
ON
L VSCS R
ON
OFF
OFF
TEST
UTILITY PANEL
OFF
ALT
RIGHT OFF
LEFT OFF
NACA
INLET
CLOSE
ELECTRICAL MASTER
L GEN
ON
OFF
OFF
R GEN
ON
OFF
RESET
VENT
HIGH
SYS 2
O
F
F
AVIONICS
ON
VENT
LOW
PITOT
HEAT
BOTTLE
DISCHARGE
PRI
OFF
COOL
LOW
COOL
HIGH
POWER
BAT/EXT
OFF
NOTE: FOR
AIRCRAFT WIT
AND NACA INL
NORMAL
ESNTL
RESET
ESSENTIAL BUS
GCU
LIGHTING CONTROL
LT MSTR
ON
IIDS
CONSOLE
L
XMSN
FIRE
R
5
5
5
FUEL VLV
L
OFF
OFF
FLOOD
STROBE
POSN
ON
ON
OFF
OFF
OFF
BOTH
CKP
INSTR
XFD
R
L
R
BLD AIR
LEAK
5
5
5
TRIM
PITOT
HEAT 1
BLD AIR
HEAT
5
5
IIDS
FUEL
PROBE
LAND
LGT
5
10
AREA
7
CAB
OFF
AUDIO
PNL 1
VSCS
7
5
ENG FIRE
5
NAV
COM 1
5
INST STBY
FLOOD ATT
5
XPNDR
DIR
1
GYRO 1
7
STROBES
RED
WHITE
OFF
Figure 4−4. Switches and Circuit Breakers − Console Mounted (Typical)
4−18
FAA Approved
Reissue 3
Revision 2
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LEFT GENERATOR BUS
AUDIO
PNL2
CRGO
HOOK
EVAP
VENT
EVAP
BATTERY BUS
CKPT
UTIL
CAB
UTIL
L
COMP
PITOT
HEAT2
L
CNDSR
FAN 2
CNSL
ATT
GYRO2
Normal Procedures
R
R
DETENT
LIGHT
MSTR
RIGHT GENERATOR BUS
L
BST PMP
INSTR
AV
MSTR
EEC
R
FUEL
LOW
OFF
GATE
L
POSN
STROBE
RTR
BRK
FIRE
HRD
LIGHTING
IGNTR
R
AREA
20
IIDS
TRAK
STB
CFU
AV
FAN
IPS
ATT
GYRO1
LAND
LGT
CNDSR
FAN 1
ENC
ALT
L FLD
EXCIT
LEFT AVIONICS BUS
HOV
SRCH LT SRCH LT
NACA
RT FLD
EXCIT
RIGHT AVIONICS BUS
ADF2
RADAR
RT
RADAR
IND
RADAR
INVTR
RAD
ALT
ADF1
FM
CTRL
FM1
RT
MKR
BCN
COM2
XPNDR
2
DIR
GYRO2
NAV 2
DME
LORAN
GPS
FM2
RT
FM3
RT
F90−030B
Figure 4−5. Circuit Breakers − Baggage Compartment Mounted (Typical)
FAA Approved
Reissue 3
Original
4−19
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
5
4
1. COLLECTIVE FRICTION RELEASE
2. EEC RESET SWITCH
3. NP SWITCH
4. HOVER AND LANDING LIGHT SWITCH
5. SEARCH LIGHT SWITCH (SEE NOTE)
6. GO-AROUND SELECT SWITCH
7. COMMUNICATIONS SELECT SWITCH
8. BLANK
9. VSCS SYNCHRONIZATION SWITCH
10. LEFT/RIGHT ENGINE TWIST GRIPS
11. INDEX MARKS
12. ALIGNMENT MARK
LIGHTS
LDG
EXT
HVR
OFF
L
6
R
GA
ÊÊ
ÊÊ
ÊÊ
EEC
HIGH
3
NORM
R
P
M
UP
RET
L
RESET
R
7
COM
1
DOWN
2
1
COM
2
8
2
NOTE: IF SEARCHLIGHT IS INSTALLED, POWER
IS PROVIDED WITH HOVER AND
LANDING LIGHT SWITCH IN HVR OR
LDG POSITION.
L
11
N
O
R
M
A
L
9
10
N
O
R
M
A
L
R
12
11
1
F90−031C
Figure 4−6. Collective Pitch Stick Controls
4−20
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
AUTO PILOT
DISENGAGE
RADIO/ICS
CARGO HOOK
RELEASE
CYCLIC TRIM
FLOAT INFLATION
SWITCH
F90−032
Figure 4−7. Cyclic Stick Grip
FAA Approved
Reissue 3
Original
4−21
CSP−900RFM206A−1
Normal Procedures
4−4.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENGINE PRE−START COCKPIT CHECK
ELECTRICAL POWER − OFF
All cabin doors closed and safelocked
Seat belt and shoulder harness for proper fit and engage­
ment of buckle
Operation of shoulder harness inertia lock
Rotor brake
Magnetic compass
Flight instruments
Collective Control:
CHECK
FASTENED
CHECK
STOWED
CHECK
CHECK STATIC
POSITION/SET
Collective friction
ON
Collective stick position
FULL DOWN
CAUTION
If collective is not full down, do not try to force down until hydraulic
pressure increases during start. Sufficient hydraulic pressure will
be available when NR is above 25 percent.
Twistgrip alignment marks aligned with
index mark
CHECK
LDG/HVR lights
OFF
ON
Key switch
Essential bus panel:
IN
Circuit breakers
NACA inlet panel (if installed):
NORMAL
NACA inlet switch
Utility panel:
CAB HEAT
OFF
AC/VENT
OFF
PITOT HEAT (if installed)
OFF
IPS (if installed)
OFF
VSCS L/R
ON
Lighting control panel:
4−22
AS REQUIRED
LT MSTR
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CONSOLE/IIDS/FLOOD/INSTR
AS DESIRED
STROBE/POSN/AREA
AS DESIRED
CSP−900RFM206A−1
Normal Procedures
NOTE: If white strobe lights are installed, the “BOTH” or “WHITE” switch positions are
to be used during daytime operations only. (Ref. Figure 4−4.)
Electrical master panel:
Avionics
AS DESIRED
L GEN and R GEN
ON (OFF FOR GPU START)
POWER
OFF
Fuel system panel:
L BOOST AND R BOOST
OFF
CROSS FEED
OFF
LEFT/RIGHT FUEL SHUTOFF
ON; COVER CLOSED
Engine control panel:
OFF
L ENGINE and R ENGINE
ELECTRICAL POWER − ON
Electrical master panel:
POWER
IIDS:
BAT/EXT
FIRE WARNING ANNUNCIATORS
ON FOR 2 SECONDS; CHECK IIDS
FOR ADVISORIES
Monitor BIT
NOTE: Perform a commanded IIDS BIT if the helicopter has been statically exposed to
temperatures below 0°C for 12 hours or longer.
Fuel quantity display
CHECK
DISP (display by exception)
AS DESIRED
NACA position lights (if installed)
FAA Approved
Reissue 3
Revision 2
LH/RH NACA DOORS CLOSED
4−23
CSP−900RFM206A−1
Normal Procedures
4−5.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENGINE STARTING − AUTOMATIC
NOTE: Either engine may be started first.
Engine starts have been demonstrated at temperatures as low as −36°C with a
ground power unit (GPU) assisted by the aircraft battery.
Engine starts using battery power only have been demonstrated after the aircraft
and battery have been statically exposed to temperatures down to 0°C for 12
hours or more.
A GPU should be used in lieu of aircraft battery power when attempting more
than one initial engine start during operations in ambient temperatures above
32°C.
Maximum demonstrated wind speed for starting and stopping the rotor is 50
knots.
Fuel system panel:
EEC MAN indicators
Engine control panel:
ON; CHECK IIDS INDICATION
L BOOST or R BOOST
OFF
SET TO IDLE/FLY AS REQUIRED
L ENGINE or R ENGINE
CAUTION
Monitor EGT, NG, and starter limits during start. If EGT is observed
rising above 700°C, abort the start as follows.
Engine control switch OFF; monitor IIDS displays.
If lightoff is not attained with an increase of EGT and NG within
10 seconds, place the engine control switch to off. Following a
30 second fuel drain period, perform a 30 second dry motoring
run (Ref. Section VIII) before attempting another start. Repeat the
complete starting sequence observing limitations. This procedure
applies to ground and air−starts in the auto mode.
Ensure collective full down, cyclic (Ref. Figure 4−9) and pedals
centered as hydraulic pressure increases. Should an abnormal
vibration occur as the NR passes through 35 to 40%, shutdown
aircraft and advise maintenance. This vibration may indicate that
possible damage to the flexbeam has occurred.
If collective is not full down, do not try to force down until hydraulic
pressure increases during start. Sufficient hydraulic pressure will
be available when NR is above 25 percent.
4−24
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Normal Procedures
CHECK FOR NORMAL INDICATIONS
IIDS
NOTE: Do not start second engine until at least 60% NR is attained on the first engine.
Repeat starting procedure for second engine
GPU start only:
L GEN/R GEN
ON
GPU
DISCONNECT
4−6.
ENGINE RUNUP
Electrical master panel:
Engine control panel:
4−7.
ON, AS DESIRED
Avionics
FLY
L ENGINE and R ENGINE
BEFORE TAKEOFF
Cyclic response check:
Primary and secondary IIDS displays
Collective control:
Move cyclic stick and observe rotor tip for correct movement.
NP switch
CHECK ADVISORIES
HIGH
NOTE: To increase or decrease operating RPM, press and hold switch momentarily.
Confirm desired RPM changes on IIDS primary display.
Utility Panel:
Collective friction
PITOT HEAT (if installed)
AS DESIRED
AS REQUIRED
NOTE: Turn pitot heat on when visible moisture conditions prevail and OAT is 5°C and
below.
IPS switch (if installed)
AS DESIRED
CAB HEAT
AS DESIRED
FAA Approved
Reissue 3
Original
4−25
CSP−900RFM206A−1
Normal Procedures
4−8.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TAKEOFF
Hover area and takeoff path
CLEAR
Hover power
NOTE TORQUE
Takeoff
PERFORM, USING UP TO 10% ABOVE
HOVER POWER
NP Switch
SET TO NORM AS AIRSPEED
INCREASES ABOVE 47 KIAS
NOTE: For takeoff in noise−sensitive areas, refer to Paragraph 4−14.
NOTE: With the Range Extender filler installed and the fuel system ‘‘topped off’’, the IIDS
fuel quantity will not display a decrease until after approximately 10 minutes of
flight.
4−9.
CRUISE
NACA doors (if installed) may be closed if blowing dust, sand, etc. is present in
the atmosphere.
IPS switch (if Inlet Particle Separator installed) may be turned OFF.
NOTE: Decision to use the inlet particle separator scavenge air should be based on
atmospheric conditions, gross weight and height above terrain where operations
are to be conducted.
If desired, press the VSCS Synchronization switch left or right for three seconds
to reset the VSCS to the current lateral acceleration and yaw rate.
4−10. SLOW FLIGHT/APPROACH
When operating below 47 KIAS, the engine/rotor system is to be operated at 104
percent. (This reduces the rotor torque and reduces the anti-torque requirement.)
The IIDS and the NACA door actuators (if installed) receive a discrete input from
an airspeed switch in the airspeed indicator and the IIDS displays the message
``BEEP TO 104%” on the alphanumeric display. This signals the IIDS to rescale
the NP/NR vertical scales so that 104% rpm is in the green operating range and
the NACA doors to automatically close. When airspeed increases above 47 KIAS,
the NP/NR rescales so that 100% rpm is in the green range and the NACA doors
open.
NOTE: In the event that the IIDS fails to display ‘‘BEEP TO 104%’’, or the NP/NR fails
to rescale, the pilot is still required to follow the correct procedure and operate
the NP switch as follows.
When airspeed decreases below 47 KIAS:
NP Switch
HIGH
NACA door indicator light (if installed)
LH/RH NACA DOOR CLOSED
4−26
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
NOTE: If NACA indicator light(s) indicates OPEN, inlet air will bypass the IPS, allowing
unfiltered air into the compresor inlet.
When the helicopter airspeed increases above 47 KIAS:
NP Switch
NORM
NACA door indicator light (if installed)
LH/RH NACA DOOR OPEN
NOTE: If NACA indicator light(s) indicates CLOSED, engine EGT(s) will be slightly
higher.
4−11. LANDING
Use the illustration below to determine safe landing attitudes. Nose up attitudes
in excess of 9° 40′ will result in the tail skid contacting the landing surface.
9° 40′
30.16 IN
(76.61cm)
F927−098A
Figure 4−8. Tail Skid to Landing Surface Clearance
Running landing:
Maximum recommended ground contact speed is 30 knots for smooth hard sur­
face.
Avoid rapid lowering of the collective and aft cyclic after ground contact.
Slope landing:
Slope landings have been demonstrated up to 12° in any direction. Successful
completion of this maneuver on a particular surface will depend on sufficient
friction between the skid tubes and the landing surface to prevent the helicopter
from sliding.
FAA Approved
Reissue 3
Original
4−27
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
4−12. ENGINE/AIRCRAFT SHUTDOWN − NORMAL
NOTE: Shut down the engines before exiting the helicopter unless safety or operational
considerations dictate otherwise.
Maximum demonstrated wind speed for starting and stopping the rotor is 50
knots.
Collective stick
FULL DOWN; FRICTION ON
Cyclic stick
TRIM TO NEUTRAL
(REF FIGURE 4−9)
Pedals
NEUTRAL
Engine control panel
SET TO IDLE
L ENGINE and R ENGINE
All unnecessary electrical equipment
Utility panel:
OFF
Heat
OFF
AC (if installed)
OFF
Pitot heat (if installed)
OFF
IPS (if installed)
OFF
Lighting control panel
Electrical master panel:
AS DESIRED
Avionics master switch
OFF
L GEN/R GEN switches
OFF
Fuel system panel:
OFF
L BOOST/R BOOST
Engine control panel:
OFF
L ENGINE and R ENGINE
CHECK IIDS
ENG OUT indications
CAUTION
4−28
Do not use collective pitch to slow rotor.
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
If there is evidence of post engine high EGT, follow the dry run
procedure as described below.
WARNING
CAUTION
Normal Procedures
Should an abnormal vibration occur as the NR passes through 40
to 35%, advise maintenance before further flights. This vibration
may indicate that possible damage to the flexbeam has occurred.
NOTE: Check that compressor decelerates freely. Abnormal noise or rapid run down
(rapid loss of NG) may indicate turbine blade rubbing.
Dry run procedure:
Twist grip
OFF
Engine control switch for selected engine
SET TO IDLE −
OBSERVE STARTER
TIME LIMITS
Engine control switch for selected engine
OFF
Normal shutdown continued:
Rotor brake (if installed):
Raise brake handle to release from stowed position
Rotate handle clockwise and apply brake by pulling
down on handle until handle locks aft. Release rotor
brake during last revolution unless conditions dictate
otherwise.
CAUTION
APPLY BELOW
70% NR
Care should be taken while applying the rotor brake if the helicopter
is parked on a slippery or icy surface. Anti−torque control is
minimized at less than normal operating RPM when the engine is
not driving the rotor system. Full control of the helicopter during
these conditions may be limited.
CHECK FOR
INDICATIONS OR
MESSAGES
IIDS
NOTE: Wait for NG to reach 0% before entering the IIDS “Time Summary” menu to check
“LST FLT TIME” or “TOT FLT HR”. Failure to wait for NG to reach 0% may result
in incorrect time records.
Electrical master panel:
OFF AT 0% NG
POWER
AS DESIRED
Key Switch
FAA Approved
Reissue 3
Original
4−29
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CENTERING STRAP IN
EXTENDED POSITION
90°
CENTERING DECAL
CENTERING STRAP IN
STOWED POSITION)
CENTERING STRAP
CAUTION: CYCLIC SHOULD BE TRIMMED TO THE NEUTRAL POSITION FOR START-UP AND SHUTDOWN.
NEUTRAL POSITION IS ACHIEVED WITH CENTERING STRAP EXTENDED, TOUCHING CENTERING DECAL WHEN PERPENDICULAR TO INSTRUMENT PANEL.
F90−135A
Figure 4−9. Cyclic Centering
4−13. POST FLIGHT
Aircraft-investigate any suspected damage
CHECK
Rotor blades
CHECK BLADE
RETENTION BOLTS
(PINS)
Fuel and oil leaks
CHECK
Engine and rotor transmission oil levels
CHECK
NOTE: Engine oil level should be checked within 10 minutes after shutdown.
Fuel catch cans (installed)
DRAIN INTO
SUITABLE
CONTAINER
Logbook entries
COMPLETE
Flight manual and equipment
STOWED
Aircraft tiedowns, covers
AS REQUIRED
4−30
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
4−14. NOISE IMPACT REDUCTION PROCEDURES
Safe operation of the helicopter always has the highest priority.
Utilize the following procedures only when they will not conflict
with safe helicopter operation.
Certain flight procedures are recommended to minimize noise impact on surrounding
areas. It is imperative that every pilot subject the public to the least possible noise
while flying the helicopter.
Takeoff:
CAUTION
Takeoff using maximum takeoff power at the speed for best rate of climb (Ref.
Section V).
Proceed away from noise sensitive areas.
If takeoff must be made over noise sensitive area, distance (altitude) is the best
form of noise suppression.
Cruise:
Maintain 1000 feet minimum altitude where possible.
Maintain speed of no more than 110 knots over populated areas.
Coordinated turns at around the speed for best rate of climb cause no appreciable
change in noise.
Sharper turns reduce area exposed to noise.
Approach:
Use steepest glideslope consistent with passenger comfort and safety.
Noise characteristics data is provided in Section V.
FAA Approved
Reissue 3
Original
4−31
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
4−15. FLIGHT WITH DOORS REMOVED OR CABIN DOORS OPEN
CAUTION
Stow or secure all loose objects with doors opened or removed.
The aircraft may be flown with cabin doors open or removed in accordance with
the flight restrictions stated in Section II.
NOTE: Refer to Section VI for weight and balance data with doors opened or removed.
One or both cabin doors may be opened or closed in flight at airspeeds up
to 60 KIAS.
For sustained flight with the cabin doors open, use of the cabin door hold
open device is required (Ref. Figure 4-10).
CABIN DOOR HOLD
OPEN DEVICE
(STOWED)
CABIN DOOR
RESTRAINT FITTING
CLIP
LEFT SIDE, LOOKING INBOARD
NOTE: THE CABIN DOOR HOLD OPEN DEVICE
OPERATES BY ATTACHING TO THE FORWARD CABIN
DOOR RESTRAINT WHEN THE DOOR IS IN THE FULLY
OPEN POSITION.
Figure 4−10. Cabin Door Hold Open Device
4−32
FAA Approved
Reissue 3
Original
F90−125
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Normal Procedures
4−16. ONE ENGINE INOPERATIVE TRAINING
Placing an engine control switch in the TRAIN position will simulate a one engine
inoperative (OEI) condition by resetting the selected engine's governed speed to
92 percent NP, thereby putting the engine on standby while allowing single engine
training on the opposite engine. In the event of an engine failure (or inadvertent
switching to IDLE) on the opposite engine, the engine in TRAIN will automatically
revert to 100/104% NP. Also, if the opposite engine control switch is placed in TRAIN
both engines will revert to 100/104% NP.
When operating with one engine in the train mode OEI limits apply. However the
TORQUE and EGT displays do NOT rescale to OEI limits nor is the ENG OUT
warning activated. OEI limits are generally considered for ``emergency use only''
and excursions into those limits require recording in the engine log book and may
increase the maintenance required. See Section VIII for recording and maintenance
action requirements. Pilots should consider such things as flight mode, gross weight,
density altitude and aircraft familiarity before conducting OEI training to avoid
excursions into the OEI limits.
Recommended maximum takeoff weight for TRAIN mode operation:
6000 LBS below 5000 Ft HD
5200 LBS at or above 5000 Ft HD
If rescaling of the TORQUE and EGT displays and activation of the ENG OUT
warning is desired the pilot should select IDLE instead of TRAIN for OEI training.
In the event the opposite engine should fail during this time the pilot must select
FLY on the engine control switch to bring the good engine back to 100/104% NP.
4−17. FUEL SYSTEM
Capacities - Fuel System (Standard):
JET A: 1014 LBS; 460 KG; 149 U.S. gal; 564L total capacity
994 LBS; 146.2 U.S. gal; 553L useable
JET B: 969 LBS; 440 KG; 149 U.S. gal; 564L total capacity
950 LBS; 146.2 U.S. gal; 553L useable
Capacities - Fuel System (Range Extender):
JET A: 1097 LBS; 498 KG; 161.3 U.S. gal; 611L total capacity
1078 LBS; 158.5 U.S. gal; 600L useable
JET B: 1048 LBS; 476 KG; 161.3 U.S. gal; 611L total capacity
1030 LBS; 158.5 U.S. gal; 600L useable
FAA Approved
Reissue 3
Original
4−33
CSP−900RFM206A−1
Normal Procedures
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
4−34
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Performance Data
SECTION V
PERFORMANCE DATA
TABLE OF CONTENTS
PARAGRAPH
PAGE
5-1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-1
5-2. Noise Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-1
5-3. Density Altitude Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-1. Density Altitude Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-2
5-3
5-4. Airspeed Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-2. Airspeed Calibration Curve - Blunt Pitot Tube Installation . . . . .
5-4
5-5
5-5. Best Rate of Climb Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-3. Best Rate of Climb Speed (VY) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-6
5-7
5-6. Single Engine Rate of CLimb and Descent . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-4. Single Engine Rate of Climb and Descent, at VY, OEI MCP,
6250 LBS Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-5. Single Engine Rate of Climb and Descent, at VY, OEI MCP,
6500 LBS Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-8
5-7. Twin Engine Rate of Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-6. Twin Engine Rate of Climb, at VY, MCP,
4000 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-7. Twin Engine Rate of Climb, at VY, MCP,
4500 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-8. Twin Engine Rate of Climb, at VY, MCP,
5000 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-9. Twin Engine Rate of Climb, at VY, MCP,
5500 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-10. Twin Engine Rate of Climb, at VY, MCP,
6000 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-11. Twin Engine Rate of Climb, at VY, MCP,
6250 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-12. Twin Engine Rate of Climb, at VY, MCP,
6500 Pounds Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-8. Hover Ceiling . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-13. Controllability Envelope and Azimuth Range for
Crosswind Operations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
FAA Approved
Reissue 3
Original
5-9
5-10
5-11
5-12
5-13
5-14
5-15
5-16
5-17
5-18
5-19
5-19
5−i
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PAGE
PARAGRAPH
Figure 5-14. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power,
104% NR, Cabin Heat Off and A/C Off . . . . . . . . . . . . . . . . . . . . . . 5-21
Figure 5-15. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power,
104% NR, Cabin Heat Off and A/C On . . . . . . . . . . . . . . . . . . . . . . . 5-22
Figure 5-16. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power,
104% NR, Cabin Heat On and A/C Off . . . . . . . . . . . . . . . . . . . . . . . 5-23
Figure 5-17. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat Off and A/C Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-24
Figure 5-18. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat Off and A/C On . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-25
Figure 5-19. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat On and A/C Off . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-26
5-9. Height Velocity Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-20. Height Velocity Diagram for Operations Above
6000 LBS Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-27
5-10. Power Assurance Check - Automatic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-21. Power Assurance Check Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-28
5-28
5-11. Power Assurance Check - Manual . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-22. Engine Torque Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-23. EGT Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 5-24. NG Chart - (NG read from Secondary IIDS Display) . . . . . . . . . .
Figure 5-25. NG Chart - (NG read from Third Level Power Check Menu) . . .
5-30
5-32
5-33
5-34
5-35
5−ii
FAA Approved
Reissue 3
Original
5-27
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Performance Data
SECTION V
PERFORMANCE DATA
5−1.
GENERAL
This section contains baseline helicopter performance information as defined within
certain conditions such as airspeed, weight, altitude, temperature, wind velocity
and engine power available. Data is applicable to the basic helicopter without any
optional equipment installed unless otherwise noted.
5−2.
NOISE CHARACTERISTICS
NOTE: No determination has been made by the Federal Aviation Administration that the
noise levels of this aircraft are or should be acceptable or unacceptable for
operation at, into, or out of, any airport.
The MD900 meets the FAR Part 36-H noise requirements for level flight, takeoff/
climb, and approach descent profiles at the certified maximum gross weight of 6500
LBS.
MD900 NOISE CHARACTERISTICS
MD900
Configuration
Clean aircraft, doors on, no
external kits.
ENGINE: PW 206A
GROSS WEIGHT: 6500 LB
Level Flyover
EPNL
(EPNdB)
Takeoff
EPNL
(EPNdB)
Approach
EPNL
(EPNdB)
84.2
86.0
92.3
FAA Approved
Reissue 3
Original
5−1
CSP−900RFM206A−1
Performance Data
5−3.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
DENSITY ALTITUDE CHART
Description: The chart allows a quick estimation of the density altitude when
pressure altitude and OAT are known. This chart can also be used to determine
true airspeed.
Use of Chart:
To determine density altitude, the pilot must know pressure altitude and outside
air temperature. Enter bottom of chart with known or estimated OAT, move
up to known pressure altitude line, move to left and note density altitude.
Pressure altitude is found by setting 29.92 (1013 mb) in Kolsman window
± altimeter error.
To determine true airspeed convert indicated airspeed (IAS) to calibrated airspeed
(CAS) utilizing the Airspeed Calibration Curves (Figure 5-2). Read value on
right of chart opposite known density altitude. Multiply CAS by this value to
determine true airspeed.
Examples:
Find density altitude for 6000 HP at -15°C:
Follow -15°C line to 6,000 ft pressure altitude line; read density altitude (3800
ft).
Find density factor:
Read directly across from density altitude: (3800 ft). Note density factor of 1.058.
Find true airspeed:
130 KIAS = 127 KCAS (from Figure 5-2)
127 KCAS 1.058 = 134.4; round to 134 knots true airspeed.
5−2
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
1.36
1.34
18000
1.32
1.30
16000
1.28
1.26
14000
1.24
1.22
DENSITY ALTITUDE - FEET
12000
1.20
1.18
10000
1.16
1.14
8000
1.12
1.10
6000
1.08
4000
1.06
1.04
2000
1.02
0
1.00
0.98
-2000
-40
-30
-20
-10
0
10
20
30
40
50
60
TEMPERATURE - °C
-40 -30 -20 -10 0
10
20
30
40
50
60
TEMPERATURE - °F
70
80
90
100 110 120
130 140
F90−104A
Figure 5−1. Density Altitude Chart
FAA Approved
Reissue 3
Original
5−3
CSP−900RFM206A−1
Performance Data
5−4.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AIRSPEED CALIBRATION
Description: These charts show the difference between indicated and calibrated
airspeeds.
Indicated airspeed (IAS) corrected for position error equals calibrated airspeed
(CAS).
Use of chart: Use the chart as illustrated by the example. To determine calibrated
airspeed, the pilot must know the indicated airspeed.
NOTE: The example below refers to Figure 5−2.
Example:
Wanted: Calibrated airspeed
Known: Indicated airspeed = 120 knots
Method: Enter the bottom of the chart at the indicated airspeed of 120 knots.
Move up to the airspeed calibration line; move left and read 117 knots,
calibrated airspeed.
5−4
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
160
140
CALIBRATED AIRSPEED - KNOTS
120
100
80
60
40
20
20
40
60
80
100
120
140
INDICATED AIRSPEED - KNOTS
160
F90−102−3A
Figure 5−2. Airspeed Calibration Curve − Blunt Pitot Tube Installation
FAA Approved
Reissue 3
Original
5−5
CSP−900RFM206A−1
Performance Data
5−5.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
BEST RATE OF CLIMB SPEED
Description: This chart shows the indicated airspeed to use for the best rate of
climb at any given density altitude.
Use of Chart: Use the chart as illustrated by the example below.
Example:
Wanted: Best rate of climb
Known: Density altitude = 8,000 feet
Method: Enter the left side of chart at the known density altitude of 8,000 feet.
Move to the right to the airspeed calibration curve and then directly
down to read 60 knots indicated airspeed (IAS) as the best rate of climb
speed.
5−6
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
18000
16000
14000
DENSITY ALTITUDE - FEET
12000
10000
8000
6000
4000
2000
0
20
25
30
35
40
45
50
55
60
INDICATED AIRSPEED - KNOTS
65
70
75
80
F90−103
Figure 5−3. Best Rate of Climb Speed (VY)
FAA Approved
Reissue 3
Original
5−7
CSP−900RFM206A−1
Performance Data
5−6.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SINGLE ENGINE RATE OF CLIMB AND DESCENT
Description: This chart shows the rate of climb vs pressure altitude at maximum
continuous OEI power, 6250 LBS gross weight, and the best rate of climb speed.
Use of Charts: Use the chart as illustrated by the example below.
Example:
Wanted: Rate of climb
Known: Pressure altitude = 2000 feet
Known: Outside air temperature = 20°C
Method: Enter the left side of chart at the known pressure altitude of 2000 feet.
Move to the right to the 20°C temperature curve and then directly down
to read rate of climb of approximately 10 feet per minute.
5−8
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
18000
17000
16000
OAT°C
15000
-36°C
14000
-30°C
13000
-20°C
-10°C
PRESSURE ALTITUDE - FEET
12000
0°C
11000
10000
10°C
9000
8000
20°C
7000
6000
30°C
5000
4000
40°C
3000
2000
MAXIMUM
OAT LIMIT
1000
50°C
0
-600
-500
-400
-200
-300
-100
RATE OF CLIMB AT VY - FT/MIN
0
100
200
F90−111D
Figure 5−4. Single Engine Rate of Climb and Descent, at VY, OEI MCP,
6250 LBS Gross Weight
FAA Approved
Reissue 3
Original
5−9
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
10000
NOTE: FOR TEMPERATURES LESS THAN 0°C, USE 0°C LINE
9000
8000
OAT
PRESSURE ALTITUDE - FEET
7000
6000
0°C
5000
10°C
4000
5000 FT HD
20°C
30°C
3000
40°C
2000
50°C
1000
MAXIMUM
OAT LIMIT
0
-500
-450
-400
-350
-300
-250
-200
-150
-100
RATE OF CLIMB/DESCENT AT VY - FT/MIN
Figure 5−5. Single Engine Rate of Climb and Descent, at VY, OEI MCP,
6500 LBS Gross Weight
5−10
FAA Approved
Reissue 3
Original
-50
0
F90-166
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
5−7.
CSP−900RFM206A−1
Performance Data
TWIN ENGINE RATE OF CLIMB
Description: These charts (Ref. Figure 5-6 thru Figure 5-11) show the rate of climb
vs pressure altitude at twin engine MCP and the best rate of climb speed.
Use of Charts: Use the charts as illustrated by the example below.
NOTE: The below example refers to Figure 5−6.
Example:
Wanted: Rate of climb
Known: Pressure altitude = 3000 feet
Known: Outside air temperature = 20°C
Method: Enter the left side of chart at the known pressure altitude of 3000 feet.
Move to the right to the 20°C temperature curve and then directly down
to read rate of climb of 2580 feet per minute.
FAA Approved
Reissue 3
Original
5−11
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
17000
OAT °C
16000
-36°C
15000
-30°C
14000
PRESSURE ALTITUDE − FEET
13000
-20°C
12000
-10°C
11000
0°C
10000
9000
10°C
8000
7000
20°C
6000
5000
30°C
MAXIMUM
OAT LIMIT
4000
ISA
3000
40°C
2000
1000
50°C
0
400
600
800
1000 1200 1400 1600 1800 2000
2200 2400
2600 2800 3000 3200 3400
3600
RATE OF CLIMB AT VY - FT/MIN
F90−131−5A
Figure 5−6. Twin Engine Rate of Climb, at VY, MCP, 4000 Pounds Gross Weight
5−12
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
OAT °C
17000
-36°C
16000
-30°C
15000
PRESSURE ALTITUDE − FEET
14000
-20°C
13000
-10°C
12000
11000
0°C
10000
9000
10°C
8000
7000
20°C
6000
5000
30°C
MAXIMUM
OAT LIMIT
4000
3000
ISA
40°C
2000
50°C
1000
0
0
200
400
600
800 1000 1200 1400 1600 1800 2000 2200 2400 2600 2800 3000 3200
RATE OF CLIMB AT VY - FT/MIN
F90−131−4A
Figure 5−7. Twin Engine Rate of Climb, at VY, MCP, 4500 Pounds Gross Weight
FAA Approved
Reissue 3
Original
5−13
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
17000
16000
OAT °C
15000
-36°C
PRESSURE ALTITUDE − FEET
14000
-30°C
13000
-20°C
12000
-10°C
11000
10000
0°C
9000
8000
10°C
7000
6000
20°C
5000
ISA
4000
MAXIMUM
OAT LIMIT
3000
30°C
2000
40°C
1000
50°C
0
0
200
400
600
800
1000
1200
1400
1600
RATE OF CLIMB AT VY - FT/MIN
1800
2000
2200
2400
2600
F90−131−3A
Figure 5−8. Twin Engine Rate of Climb, at VY, MCP, 5000 Pounds Gross Weight
5−14
FAA Approved
Reissue 3
Original
2800
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
OAT °C
17000
-36 °C
16000
-30°C
15000
14000
-20°C
PRESSURE ALTITUDE − FEET
13000
-10°C
12000
11000
0°C
10000
9000
10°C
8000
7000
20°C
6000
ISA
5000
30°C
4000
MAXIMUM
OAT LILMIT
3000
40°C
2000
1000
50°C
0
0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
2400
RATE OF CLIMB AT VY - FT/MIN
F90−131−2A
Figure 5−9. Twin Engine Rate of Climb, at VY, MCP, 5500 Pounds Gross Weight
FAA Approved
Reissue 3
Original
5−15
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
OAT °C
18000
-36 °C
17000
-30°C
16000
15000
-20°C
14000
-10°C
PRESSURE ALTITUDE − FEET
13000
12000
0°C
11000
10000
10°C
9000
8000
20°C
7000
6000
30°C
ISA
5000
4000
40°C
3000
MAXIMUM
OAT LIMIT
2000
1000
0
50°C
0
200
400
600
800
1000
1200
1400
1600
1800
2000
2200
RATE OF CLIMB AT VY - FT/MIN
F90−131−1A
Figure 5−10. Twin Engine Rate of Climb, at VY, MCP, 6000 Pounds Gross Weight
5−16
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
17000
16000
15000
14000
OAT °C
-30°C
PRESSURE ALTITUDE − FEET
13000
-36 °C
12000
11000
10000
-20°C
9000
-10°C
8000
0°C
7000
10°C
6000
20°C
5000
4000
ISA
30°C
3000
2000
40°C
MAXIMUM
OAT LIMIT
1000
50°C
0
0
200
400
600
800
1000
1200
RATE OF CLIMB AT VY - FT/MIN
1400
1600
1800
2000
2200
F90−131−6
Figure 5−11. Twin Engine Rate of Climb, at VY, MCP, 6250 Pounds Gross Weight
FAA Approved
Reissue 3
Original
5−17
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
20000
19000
18000
17000
14000 FT HD
LIMIT
16000
15000
14000
OAT
13000
PRESSURE ALTITUDE − FEET
12000
-36 °C
11000
-30°C
10000
-20°C
9000
-10°C
8000
0°C
7000
10°C
6000
20°C
5000
30°C
4000
3000
40°C
2000
MAXIMUM
OAT LIMIT
1000
50°C
0
0
200
400
600
800
1000
1200
1400
RATE OF CLIMB AT VY - FT/MIN
1600
1800
2000
2200
F90-167A
Figure 5−12. Twin Engine Rate of Climb, at VY, MCP, 6500 Pounds Gross Weight
5−18
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
5−8.
HOVER CEILING
Description:
The hover ceiling charts show the maximum hover weight capability, in ground
effect (IGE) or out of ground effect (OGE), both engines operating at take off power
for known conditions of pressure altitude and outside air temperature, or alternately,
the maximum hover ceiling for a known gross weight and outside air temperature.
MAXIMUM SAFE WINDS FOR HOVER OPERATIONS DECREASE WITH
INCREASING DENSITY ALTITUDE. TAKEOFF AND LANDING OPERATIONS IN
CALM WINDS OR HEADWINDS
ÔÔÔÔÔÔÔÔÔÔÔÔ
ÔÔÔÔÔÔÔÔÔÔÔÔ
ÔÔÔÔÔÔÔÔÔÔÔÔ
ÔÔÔÔÔÔÔÔÔÔÔÔ
ÔÔÔÔÔÔÔÔÔÔÔÔ
ÔÔÔÔÔÔÔÔÔÔÔÔ
12400
12000
11000
DENSITY ALTITUDE - FEET
10000
9000
IGE HOVER OPERATION
LIMITED TO 15 KNOTS
WHEN WIND IS FROM
AZIMUTH RANGE `A', OR 17
KNOTS WHEN WIND IS
FROM AZIMUTH RANGE “B”
(SEE FIGURE BELOW).
IGE HOVER OPERATION IN WINDS
IN EXCESS OF 17 KNOTS HAVE
BEEN
DEMONSTRATED
IN
AZIMUTH RANGE “C”
(SEE FIGURE BELOW).
8000
7000
6000
IGE HOVER OPERATION IN
WINDS OF 17 KNOTS HAVE
BEEN DEMONSTRATED FOR ALL
AZIMUTHS UP TO THIS LINE.
5000
4000
3000
2000
1000
0
4000
4200
4400
4600
4800
5000
5200
5400
5600
5800 6000
6250
6500
6200 6400
6600
GROSS WEIGHT - LBS
0°
C
80°
C
270°
17 KTS
B
A
15 KTS
C
120°
17 KTS
B
135°
AZIMUTH RANGE
F927−146C
190°
Figure 5−13. Controllability Envelope and Azimuth Range for Crosswind Operations
FAA Approved
Reissue 3
Original
5−19
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Hover ceiling charts apply to helicopters equipped with either the inlet particle
separator (IPS) or screen inlet.
Hover ceiling charts with ``A/C On'' apply to MDHS P/N 900P7250302-101 air‐condi­
tioning installation only.
NOTE: If optional IPS is installed, reduce gross weight capability by 100 LBS for
operations with the IPS switch ON.
Baseline electrical load is 15% per generator (30 amps per generator). Reduce
gross weight capability by 35 lbs for each 10% increase in total load.
For many operations, a reduction in gross weight capability still allows the aircraft
to operate at a maximum gross weight of 6500 lbs. Follow the example shown
below.
Use of Chart: The following example explains the correct use of the IGE Chart
in Figure 5-14.
Example:
Wanted: Maximum gross weight for hover at 3.5 feet skid height at takeoff power.
Known: PA = 6000 feet; OAT = 24°C; cabin heat and A/C off; IPS ON; 25% electrical
load.
Method: Enter the chart at 24° OAT and move vertically to the 6000 PA curve
(dashed lines). At this point, move directly to the left of the chart and
read from the gross weight scale 6337 pounds.
Reduce gross weight by 100 lbs for IPS ON and an additional 35lbs
for increased electrical load. Gross weight for hover is 6202 lbs.
CAUTION
Gross weight data above 6500 LB has been provided for calculation
purposes or external load operations only. Weights above 6500
LB must be external and jettisonable. For IGE hover operations,
observe 5000 FT HD limit when operating at weights from 6251 to
6500 LB.
The instructions for using the IGE hover ceiling charts also apply to the OGE
hover ceiling charts.
5−20
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
4800
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
11000
4900
10000
12000
5000
GROSS WEIGHT − LB
5100
9000
13000
5200
8000
5300
14000
5400
16000
7000
15000
6000
5500
5600
5000
5700
4000
5800
5900
3000
6000
2000
6100
1000
6200
6300
6400
6500
6600
−40
−30
−20
−10
0
10
20
30
40
50
60
OAT °C
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
F90−105F
Figure 5−14. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power, 104% NR,
Cabin Heat Off and A/C Off
FAA Approved
Reissue 3
Original
5−21
CSP−900RFM206A−1
Performance Data
4700
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
11000
4800
12000
4900
10000
5000
9000
GROSS WEIGHT − LB
5100
13000
5200
5300
8000
14000
5400
16000
7000
15000
6000
5500
5000
5600
5700
4000
5800
3000
5900
6000
2000
6100
1000
6200
S.L.
6300
6400
6500
6600
−40
−30
−20
−10
0
10
20
30
40
50
60
OAT °C
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
F90−107E
Figure 5−15. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power, 104% NR,
Cabin Heat Off and A/C On
5−22
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
4400
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
4500
4600
11000
12000
4700
PRESSURE ALTITUDE - FEET
10000
4800
13000
4900
9000
GROSS WEIGHT − LB
5000
14000
5100
15000
5200
8000
16000
5300
MAXIMUM
TEMPERATURE FOR
CABIN HEAT ON
5400
7000
5500
5600
6000
5700
5800
5900
5000
6000
6100
4000
6200
6300
6400
6500
6600
−40
−30
−20
−10
0
10
OAT °C
20
30
40
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
50
60
F90−108E
Figure 5−16. Hover Ceiling, IGE, 3.5 Foot Skid Height, Takeoff Power, 104% NR,
Cabin Heat On and A/C Off
FAA Approved
Reissue 3
Original
5−23
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
4600
4700
GROSS WEIGHTS ABOVE 6500
LBS MUST BE EXTERNAL AND
JETTISONABLE
11000
12000
10000
4800
9000
13000
4900
5000
8000
14000
5100
16000
15000
7000
5200
6000
5300
5000
GROSS WEIGHT − LB
5400
5500
4000
5600
5700
3000
5800
2000
5900
1000
6000
SL
6100
6200
6300
MAXIMUM
INTERNAL
GROSS
WEIGHT
6400
6500
6600
6700
6800
6900
7000
7100
7200
−40
−30
−20
−10
0
OAT °C
10
20
30
40
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
Figure 5−17. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat Off and A/C Off
5−24
FAA Approved
Reissue 3
Original
50
60
F90−109E
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
11000
4600
4700
4800
12000
GROSS WEIGHTS ABOVE 6500
LBS MUST BE EXTERNAL AND
JETTISONABLE
10000
9000
13000
4900
8000
5000
5100
16000
15000
14000
7000
5200
6000
5300
5000
5400
4000
GROSS WEIGHT − LB
5500
5600
3000
5700
2000
5800
5900
1000
6000
SL
6100
6200
6300
MAXIMUM
INTERNAL
GROSS
WEIGHT
6400
6500
6600
6700
6800
6900
7000
7100
7200
−40
−30
−20
−10
0
OAT °C
10
20
30
40
50
60
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
F90−106E
Figure 5−18. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat Off and A/C On
FAA Approved
Reissue 3
Original
5−25
CSP−900RFM206A−1
Performance Data
4200
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
THIS CHART BASED ON WINDS 3KTS OR LESS AND 15% ELECTRICAL LOAD. FOR ELECTRICAL LOADS ABOVE/BELOW 15%,
DECREASE/INCREASE WEIGHT CAPABILITY 35 LBS PER 10% CHANGE IN ELECTRICAL LOAD.
REDUCE WEIGHT CAPABILITY BY 100 LBS FOR IPS ON. (SEE EXAMPLE)
4300
PRESSURE ALTITUDE - FEET
11000
4400
12000
4500
4600
4700
10000
GROSS WEIGHTS ABOVE 6500
LBS MUST BE EXTERNAL AND
JETTISONABLE
4800
4900
16000
5000
15000
13000
9000
14000
8000
5100
5200
7000
5300
GROSS WEIGHT − LB
5400
6000
MAXIMUM
TEMPERATURE FOR
CABIN HEAT ON
5500
5600
5000
5700
5800
4000
5900
6000
6100
6200
6300
6400
3000
MAXIMUM
INTERNAL
GROSS
WEIGHT
2000
6500
6600
1000
6700
6800
6900
SL
7000
7100
7200
−40
−30
−20
−10
0
OAT °C
10
20
30
40
NOTE: MAXIMUM INTERNAL GROSS WEIGHT 6500 LB. WEIGHTS IN EXCESS OF 6500 LB MUST BE EXTERNAL AND JETTISONABLE.
Figure 5−19. Hover Ceiling, OGE, Takeoff Power, 104% NR,
Cabin Heat On and A/C Off
5−26
FAA Approved
Reissue 3
Original
50
60
F90−110F
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
5−9.
HEIGHT VELOCITY DIAGRAM
Operations above 6000 LBS gross weight:
The cross hatched area represents airspeed/altitude combinations to be avoided.
160
140
ALTITUDE - AGL (FEET)
120
100
80
60
40
20
0
SMOOTH, HARD
SURFACE - WIND CALM
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
ÌÌÌÌÌÌÌÌ
ÓÓÓÓÓÓÓÓ
ÌÌÌÌÌÌÌÌ
ÓÓÓÓÓÓÓÓ
ÌÌÌÌÌÌÌÌ
ÓÓÓÓÓÓÓÓ
ÌÌÌÌÌÌÌÌ
ÓÓÓÓÓÓÓÓ
ÌÌÌÌÌÌÌÌ
ÓÓÓÓÓÓÓÓ
ÓÓÓÓÓÓÓÓ
6251 TO 6500 LB
AVOID AREA
0
5
6001 TO 6250 LB
AVOID AREA
10
15
20
AIRSPEED - KNOTS
F90−134A
25
30
Figure 5−20. Height Velocity Diagram for Operations Above 6000 LBS Gross Weight
Operations at 6000 LBS gross weight or less:
There is no height-velocity diagram for operating between sea level and 7000
feet density altitude. Safe landings and single engine fly-aways following an
engine failure have been demonstrated for the conditions stated below.
Safe landings following a vertical descent were demonstrated at sea level, 6000
lbs. gross weight, up to 50 ft. skid height.
Fly-aways were demonstrated at sea level, 6000 lbs. gross weight, from 50 ft.
skid height.
Safe landings following a vertical descent were demonstrated at 7000HD, 6000
lbs. gross weight, up to 50 ft. skid height.
Safe run-on landings were demonstrated at 7000 HD, 6000 lbs. gross weight,
and 75 ft. skid height.
Fly-aways were demonstrated at 7000 HD, 6000 lbs. gross weight, and 100 ft.
skid height.
FAA Approved
Reissue 3
Original
5−27
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
5−10. POWER ASSURANCE CHECK − AUTOMATIC
The power assurance check provides a means for the pilot to determine, prior to
take off, that each engine is capable of developing specification power.
NOTE: The primary purpose of this chart is its use as an engine performance trending
tool to aid in determining whether the engine is producing specification power,
or if engine power deterioration has occurred. Power check data taken at regular
intervals should be plotted to monitor trends in engine condition. Any trend
indicating a reduction in engine performance should be investigated.
If desired, pilots can view the last powercheck under the IIDS POWER CHECK
menu or other previous power assurance checks in the TREND LOG under AIR­
CRAFT MONITOR menu.
NOTE: This power check procedure refers to the automated IIDS power check. If unable
to perform the automated power check, use the manual power check method
found in paragraph 5−11.
TOP LEVEL
SECOND LEVEL
THIRD LEVEL
FOURTH LEVEL
AUTOMATIC
POWER CHECK
PERFORM POWER
ASSURANCE CHK
GND POWER CHK
LFT ENG TQ XXX.X%
TIME 30 SEC
NOTE 1
VIEW LAST POWER
ASSURANCE CHK
AUTOMATIC
LT NG = XXX.X%
RECORD DONE
RT NG = XXX.X%
PRESS REC
L PA CHK NG-X.X
L PA CHK EGT-XX.X
L PA CHK NG-X.X
L PA CHK EGT-XX.X
AUTOMATIC
R PA CHK NG-X.X
R PA CHK EGT-XX.X
RT ENG TQ XXX.X%
TIME 30 SEC
NOTE 2
AUTOMATIC
RECORD DONE
PRESS REC
R PA CHK NG-X.X
R PA CHK EGT-XX.X
NOTE 1: USED WHEN PERFORMING A MANUAL
POWER ASSURANCE CHECK.
NOTE2: PRESS REC KEY TO SAVE DATA IN TREND LOG;
MENU OR CLR KEY ABORTS FUNCTION
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
Figure 5−21. Power Assurance Check Menu
5−28
FAA Approved
Reissue 3
Original
F90−133
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Performance Data
HOW TO PERFORM THE CHECK:
NOTE: Power checks should be performed under the following conditions.
1. Aircraft should be faced into the wind.
2.Wind speed should not exceed 15 knots nor gust spread 5 exceed knots while
performing the check.
3.Operate engine to be checked at 100% NP for five minutes to assure proper
operating temperatures are attained.
4.IPS and CABIN HEAT should be off and the generator load should be 10% or less.
The engine to be checked should be at FLY.
The other engine should be at IDLE or OFF.
IPS and CABIN HEAT should be off and the generator load should be 10% or
less.
Select
POWER CHECK
Press the
ENT
top level menu on IIDS alphanumeric display.
key 3 times to access the fourth level menu.
LFT ENG TQ XXX.X%
TIME 30 SEC
Notice that the IIDS lists the left engine as the first engine to be checked. If
to access the
the the right engine is to be checked first, press the
right engine menu.
RT ENG TQ XXX.X%
TIME 30 SEC
Stabilize engine torque at 3% of the ENG TQ value displayed for 30 seconds.
The IIDS provides a countdown from 30 seconds on the alphanumeric display
during data acquisition. The countdown is started after the torque value is within
the 3% range for more than 2 seconds.
NOTE: Counter will reset to 15 seconds if torque setting is not maintained within 3% for
the last 15 seconds of count down.
After the IIDS calculates the performance margin of the selected engine, the
RECORD DONE
menu is displayed and advises the pilot to press the
REC
PRESS REC
key to generate a trend log (Ref. Section VII) and to display the results of the
power check on the alphanumeric display.
NOTE: If the power check fails, the IIDS displays a warning on the alphanumeric
display.
Lower collective and place engine control switch to IDLE and other engine to
FLY.
Press the
to access the right engine menu; press the
to
access the left engine menu.
Repeat check for other engine.
NOTE: The engine torque value displayed should be approximately the same as the first
engine.
FAA Approved
Reissue 3
Original
5−29
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
VIEWING THE PREVIOUS POWER CHECK:
Select
POWER CHECK
Press the
ENT
Press the
Press the
Press the
top level menu on IIDS alphanumeric display.
key once to access the second level menu.
key to enter the next second level menu.
ENT
to view the last power check.
PERFORM POWER
ASSURANCE CHK
VIEW LAST POWER
ASSURANCE CHK
L PA CHK NG-X.X
L PA CHK EGT-XX.X
key to view the results for the other engine.
R PA CHK NG-X.X
R PA CHK EGT-XX.X
5−11. POWER ASSURANCE CHECK − MANUAL
HOW TO PERFORM THE CHECK:
The engine to be checked should be at FLY (100% NR).
The other engine should be at IDLE or OFF.
IPS and CABIN HEAT should be off and the generator load should be 10% or
less.
Record the IIDS OAT and pressure altitude.
Use the Engine Torque Chart (Figure 5-22) to determine the torque value to
be utilized based on the OAT and pressure altitude recorded in the previous
step.
Increase collective and stabilize at the predetermined torque value. After one
minute, record the EGT and NG from the IIDS.
Use the EGT Chart (Figure 5-23) and the NG Chart (Figure 5-24 or Figure 5-25)
to determine maximum values of EGT and NG for the specific conditions. Subtract­
ing the recorded values from the maximum values will result in the EGT and
NG margins.
NOTE: The IIDS displays NG in tenths (ie. 91.6%) viewable at the third level of the
POWER CHECK menu.
5−30
The power check is passed if both the EGT and NG margins are greater than
or equal to zero. If either the EGT or NG margin is negative, repeat the test
allowing torque to stabilize for 5 minutes. If the EGT margin is still negative,
then the power assurance check is failed. If only the NG margin is negative refer
to the Rotorcraft Maintenance Manual for additional testing and troubleshooting.
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Performance Data
EXAMPLE:
NOTE: This example assumes the inability to access the third level POWER CHECK
menu and therfore uses Figure 5−24 to determine maximum NG value.
Recorded from the IIDS: OAT = +30°C
Pressure Altitude = 2000 ft.
Utilizing the Engine Torque Chart (Figure 5-22) the power setting for the above
noted conditions is determined to be:
Engine torque = 71%
Utilizing the EGT and NG Power Check Charts (Figure 5-23 and Figure 5-24) the
maximum values for EGT and NG for the above noted conditions is determined
to be:
EGT = 787°C
NG = 92.5%
After stabilizing the torque at 71% for one minute you record the following EGT
and NG readings from the IIDS:
EGT = 760°C
NG = 92%
Subtract the observed values of NG and EGT from the maximum values obtained
from the charts to determine the power check margins:
EGT = 787°C (from chart) minus 760°C (from IIDS) = 27°C (pass)
NG = 92.5% (from chart) minus 92% (from IIDS) = 0.5% (pass)
FAA Approved
Reissue 3
Original
5−31
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
80
SEA LEVEL
75
2000
70
4000
65
60
8000
ALTITUDE
ENGINE TORQUE (%)
PRESSURE
6000
55
(FEET)
10000
50
12000
45
14000
16000
40
35
-36
-30
-20
-10
0
10
20
AMBIENT TEMPERATURE (°C)
Figure 5−22. Engine Torque Chart
5−32
FAA Approved
Reissue 3
Original
30
40
50
F90−094−1B
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
860
SEA LEVEL
840
820
4000
PRESSURE ALTITUDE - FEET
8000
800
780
760
12000
740
16000
720
700
680
660
640
620
600
580
560
-36
-30
-20
-10
0
10
20
AMBIENT TEMPERATURE (°C)
30
40
50
F90−094−5B
Figure 5−23. EGT Chart
FAA Approved
Reissue 3
Original
5−33
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
96
95
SEA LEVEL
94
4000
PRESSURE ALTITUDE - FEET
93
8000
92
NG- %
91
12000
90
16000
89
88
87
86
85
84
83
82
81
-40 -36
-30
-20
-10
0
10
20
AMBIENT TEMPERATURE (`C)
30
40
Figure 5−24. NG Chart − (NG read from Secondary IIDS Display)
5−34
FAA Approved
Reissue 3
Original
50
F90−094−2D
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
97
SEA LEVEL
96
4000
95
PRESSURE
ALTITUDE - FEET
8000
94
12000
93
92
NG − %
91
90
16000
89
88
87
86
20000
85
84
83
−40
−30
−20
−10
0
10
20
30
40
50
AMBIENT TEMPERATURE (‘C)
60
F90−094−3
Figure 5−25. NG Chart − (NG read from Third Level Power Check Menu)
FAA Approved
Reissue 3
Original
5−35
CSP−900RFM206A−1
Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
5−36
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Weight and
Balance Data
SECTION VI
WEIGHT AND
BALANCE DATA
TABLE OF CONTENTS
PARAGRAPH
PAGE
6-1. Weight and Balance Characteristics . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-1
Table 6-1. Center of Gravity Limits . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-1
Figure 6-1. Center of Gravity Envelope. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-2
Figure 6-2. Reference Coordinates . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-3
Figure 6-3. Station Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-4
Figure 6-4. Sample Weight and Balance Record . . . . . . . . . . . . . . . . . . . . . . . . . .
6-5
Figure 6-5. Sample Weight and Balance Report . . . . . . . . . . . . . . . . . . . . . . . . . .
6-6
6-2. Load Limits and Balance Criteria . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-7
6-3. Equipment Removal or Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 6-2. Cockpit, Cabin, and Baggage Compartment Doors Weight Data . .
Table 6-3. Cabin Doors Open Weight Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-4. Longitudinal Weight and Balance Determination: Passenger Configuration . .
EXAMPLE I: Longitudinal CG Determination - Passenger . . . . . . . . . . . . . . . .
6-5. Longitudinal Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EXAMPLE II: Longitudinal CG Determination - Cargo . . . . . . . . . . . . . . . . . . .
6-6. Permissible Lateral Loadings - Passenger Configuration . . . . . . . . . . . . . . . . . . .
EXAMPLE III: Lateral CG Determination - Passenger . . . . . . . . . . . . . . . . . . . .
6-7. Lateral Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-7
6-7
6-7
6-8
6-8
6-9
6-9
6-10
6-10
6-11
6-8. Internal Loading of Cargo . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EXAMPLE IV: Tiedown 500 pounds of cargo in the main cabin. . . . . . . . . . . . .
Table 6-4. Internal Cargo Loading . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 6-6. Cargo Restraint . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 6-7. Fuel Station Diagram - Jet-A . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 6-8. Fuel Station Diagram - Jet-B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-11
6-12
6-13
6-14
6-15
6-16
Reissue 3
Original
6−i
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PAGE
PARAGRAPH
Table 6-5. Fuel Loading Table - Jet A (6.8 lb/U.S. gal) . . . . . . . . . . . . . . . . . . . . 6-17
Table 6-6. Fuel Loading Table - Jet B (6.5 lb/U.S. gal) . . . . . . . . . . . . . . . . . . . . 6-18
Table 6-7. Weight and Longitudinal Moments - Pilot, Passengers, Baggage . 6-19
Table 6-8. Weight and Longitudinal Moments - Cargo . . . . . . . . . . . . . . . . . . . . 6-20
Table 6-9. Weight and Lateral Moments - Pilot and Passengers . . . . . . . . . . . . 6-21
Table 6-10. Weight and Lateral Moments - Cargo . . . . . . . . . . . . . . . . . . . . . . . . 6-22
6−ii
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Weight and
Balance Data
CSP−900RFM206A−1
SECTION VI
WEIGHT AND BALANCE
DATA
6−1.
WEIGHT AND BALANCE CHARACTERISTICS
The weight and balance characteristics of the McDonnell Douglas MD900 helicopter
are as follows:
Maximum weight on the landing gear: 6500 pounds.
Minimum Flying Weight: 3500 pounds.
Longitudinal Reference Datum: 199.3 inches forward of rotor hub centerline (rotor
hub centerline is located at Station 199.3)
Cargo Deck Capacity: 1500 pounds not to exceed 115 pounds per square foot.
Baggage compartment limit (sta. 234.3 to 256.9): 500 pounds not to exceed 115
lbs per square foot.
Ultimate load factors (cargo restraint): Forward: 17 G's
Lateral: 8 G's
Center of Gravity Limits:
NOTE: Lateral ‘‘+’’ is right of centerline ; lateral ‘‘−’’ is left of centerline when looking
forward.
Gross Weight
Table 6−1. Center of Gravity Limits
Longitudinal C.G. Limit
(Sta-in.)
Lateral C.G. Limit
(Sta-in.)
(lb)
Forward
Aft
(+) Right, (-) Left
6500
196.0
201.4
+2.0; -2.0
6251
196.0
201.8
+2.0; -2.0
6250
196.0
203.2
±2.0
5100
196.0
206.0
±2.0
*3500
196.0
206.0
±2.0
Airspeed restrictions apply. Refer to Section II:
6250
196.0
202.1
+5.0; -2.0
5100
196.0
203.7
+5.7; -2.0
*3500
196.0
204.4
+6.0; -2.0
*Minimum flying weight.
Reissue 3
Original
6−1
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
6500
GROSS WIGHT − LBS
6000
5500
EXPANDED
CG LIMITS
5000
LATERAL CG ENVELOPE
4500
4000
NORMAL CG LIMITS
3500
3000
−3
−2
−1
0
1
2
3
4
5
6
7
CHART A: LATERAL C.G. STATION (IN.)
WHEN OPERATING IN THE
EXPANDED CG REGION OF CHART
A, THE MAXIMUM LONGITUDINAL
C.G. LIMIT, AS DEPICTED BY THE
DASHED LINE IN CHART B, APPLIES.
6500
6000
GROSS WIGHT − LBS
5100 LBS
5500
LONGITUDINAL CG ENVELOPE
5000
4500
NORMAL CG LIMITS
4000
3500
3000
194
196
198
200
202
204
206
208
CHART B: LONGITUDINAL C.G. STATION (IN)
F92−051C
Figure 6−1. Center of Gravity Envelope.
6−2
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CG REAR FACING
PASSENGERS
Weight and
Balance Data
CL OF BAGGAGE
COMPARTMENT
CG FWD FACING
PASSENGERS
CG OF PILOT OR
COPILOT/PASSENGER
CG CABIN
+19.0
+15.85
0.0
0.0
-15.85
-19.0
STA 193.0
STA 130.7
STA 173.0
STA 213.0
STA 245.6
F90−034A
Figure 6−2. Reference Coordinates
Reissue 3
Original
6−3
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
50
60
-50
40
20
0
-20
-40
-60
220
200
180
160
140
120
WL 106
FLOOR
100
80
60
BL 8.5
BEAM
60
80
100
120
140 160 180 200
STA 199.25
WL 207.97
BL 24
BEAM
220 240
260
280
300
320
340 360
380
400 420 440
460
480
5° 0”
220
200
STA 292.817
WL 147
180
160
WL 159
ROOF DECK
140
WL 106
FLOOR
120
100
80
60
3° 16”
STA 155.5
FRAME
JACKING
POINTS
STA 230.5
FRAME
F90−035D
Figure 6−3. Station Diagram
6−4
Reissue 3
Original
IN
X
OUT
ITEM NO.
REVISED CALCULATED BASIC WEIGHT
FIXED BALLAST IN NOSE
ACTUAL BASIC WEIGHT
DESCRIPTION OF ARTICLE
OR MOCIFICATION
Form HOQ014 (rev 5/00)
01/09/xx
01/09/xx
12/23/xx
DATE
AIRCRAFT MODEL
MD900
BASIC WEIGHT AND BALANCE RECORD
WEIGHT
LONG
ARM
LAT
ARM
LONG
MOMENT
LAT
MOMENT
5.0
WEIGHT
87.6
LONG
ARM
LAT
ARM
438
LONG
MOMENT
3272.8
3277.8
PAGE 4 OF 4
0.4
0.4
688665
689103
1309
1465
LONG
LAT
MOMENT MOMENT
MD Helicopters, Inc.
210.4
210.2
LAT
ARM
RUNNING TOTAL
BASIC AIRCRAFT
WEIGHT LONG
LAT
MOMENT
ARM
(CONTINUOUS HISTORY OF CHANGES IN STRUCTURE OR EQUIPMENT AFFECTING WEIGHT AND BALANCE)
SERIAL NUMBER
REGISTRATION NUMBER N9XXXX
900−000XXX
WEIGHT CHANGE
ADDED (+)
REMOVED (-)
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Reissue 3
Original
CSP−900RFM206A−1
Weight and
Balance Data
F90−115B
Figure 6−4. Sample Weight and Balance Record
6−5
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AIRCRAFT ACTUAL WEIGHT
MD900
Model
Serial No.
N92XXX
Reg. No.
Date
12/23/XX
J. Doe
Weighed by
60
900-000XX
80
100
120
140 160 180 200
STA 199.25
WL 207.97
220 240
260
280
300
320
340 360
380
400 420 440
460
480
5° 0”
220
200
STA 292.817
WL 147
180
WL 159
ROOF DECK
160
140
WL 106
FLOOR
120
100
80
60
3° 16”
STA 155.5
FRAME
JACKING
POINTS
STA 230.5
FRAME
F92−187A
EMPTY
FUEL
OIL, ENGINE LH
OIL, ENGINE RH
OIL, TRANSMISSION
HYDRAULIC FLUID
FULL
X
X
X
X
X
NOTE: IN A LEVEL ATTITUDE, MAIN ROTOR MAST IS TILTED 3 DEG. FORWARD.
WEIGHING POINT
AVE. SCALE
READING
LBS
TARE OR
CALIB. CORR.
LBS
NET
WEIGHT
LBS
LONGITUDINAL
ARM
IN
LATERAL
ARM
IN
LATERAL
MOMENT
IN-LBS
-8066
Forward
869.7
0.0
869.7
154.0
-9.3
133929
Aft Right
1289.5
0.0
1289.5
233.0
23.3
300454
29981
Aft Left
887.5
0.0
887.5
233.0
-23.3
206788
-20634
3046.7
210.4
0.4
641170
1280
-1.8
189.4
-10.4
-346
19
222.6
198.0
0.0
44071
0
3267.4
209.6
0.4
684895
1299
TOTAL (AS WEIGHED)
Less : Surplus Weight (See Table 1)
Plus: Missing Required Equipment (See Table 1)
TOTAL - BASIC WEIGHT
Figure 6−5. Sample Weight and Balance Report
6−6
LONGITUDINAL
MOMENT
IN-LBS
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
6−2.
CSP−900RFM206A−1
Weight and
Balance Data
LOAD LIMITS AND BALANCE CRITERIA
The load limits and balance conditions are as noted in Table 6-1.
Do not exceed these limitations at any time during flight.
Use the helicopter Basic Weight as recorded in the Basic Weight and Balance Record
inserted in this section to perform all weight and balance computations. Basic Weight
includes oil, hydraulic fluid, and unusable fuel.
6−3.
EQUIPMENT REMOVAL OR INSTALLATION
Removal or addition of equipment must be entered on the repair and alteration
report form, FAA 337, in accordance with Federal Air Regulations which shall then
become part of the helicopter log book file.
Record the weight and balance effects of these changes in the Basic Weight and
Balance Record inserted in this section.
Use the balance and station diagrams shown as an aid for weight and balance
changes.
Use the following tables to assist in determining weight and balance effects with
doors opened or removed.
Table 6−2. Cockpit, Cabin, and Baggage Compartment Doors Weight Data
ITEM
WEIGHT
(LB)
LONGITUDINAL
STATION
(ARM)
LATERAL
STATION
(ARM)
MOMENT
(IN−LB)
Longitudinal
Lateral
Cockpit doors (2)
24.0
132.9
"30.6
3190
"367
Cabin doors (2)
32.2
196.0
"31.2
6311
"502
9.4
269.0
Baggage door (1)
0
2529
0
Table 6−3. Cabin Doors Open Weight Data
ITEM
Cabin doors (2)
WEIGHT
(LB)
32.2
LONGITUDINAL
STATION
(ARM)
248.0
LATERAL
STATION
(ARM)
"31.2
MOMENT
(IN−LB)
Longitudinal
7986
Lateral
"502
Note: At minimum flying weight (3500 LBS) the CG shifts 0.48 inch aft with cabin doors open.
At maximum gross weight (6250 LBS) the CG shifts 0.27 inch aft with cabin doors open.
Reissue 3
Original
6−7
CSP−900RFM206A−1
Weight and
Balance Data
6−4.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LONGITUDINAL WEIGHT AND BALANCE DETERMINATION:
PASSENGER CONFIGURATION
Determine that the gross weight and longitudinal center of gravity (fore and aft)
for a given flight are within limits. Proceed as follows.
Obtain aircraft basic weight and moment from the Weight and Balance Record in­
serted in this section.
Determine weights and moments of useful load items (Ref. Figure 6-2).
Add above items.
Determine corresponding center of gravity for gross weight by dividing total moment
by gross weight. This computation must be done with zero fuel and with mission
fuel gross weight (Ref. EXAMPLE I: ).
NOTE: If loadings are not symmetrical about the aircraft centerline, determine lateral
CG’s as described in Paragraph 6−6.
EXAMPLE I: Longitudinal CG Determination − Passenger
WEIGHT
(LB)
ITEM
Basic Weight (from Figure 6-4)
STATION
(ARM)
3272.8
MOMENT
(IN−LB)
688665
Pilot
170
130.70
22219
Copilot/Passenger
170
130.70
22219
Passenger - Rear Facing R/H
170
173.0
29410
Passenger - Rear Facing L/H
170
173.0
29410
Passenger - FWD Facing R/H
170
213.0
36210
Passenger - FWD Facing L/H
170
213.0
36210
1. Zero Fuel Weight
Add: Fuel (Jet-A)
4292.8
994.0
191.1
864343
189953
2. Gross Weight
5286.8
1054296
Calculation of Longitudinal CG
CG at Zero Fuel Weight:
Moment at Zero Fuel Weight
Zero Fuel Weight
=
864343
4292.8
= 201.3
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
=
1054296
5286.8
= 199.4
NOTE: The CG’s fall within the limits specified in Table Table 6−1; therefore, the loading
meets the longitudinal CG limits.
6−8
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
6−5.
Weight and
Balance Data
LONGITUDINAL LOADING OF CARGO
The large aft compartment of the Model 900 provides great flexibility in the variety
of cargo loads it can accommodate.
To determine the gross weight and center of gravity for a given flight are within
limits, proceed as follows.
Obtain the Basic Weight and Moment from the Weight and Balance Record.
Establish the weight of cargo load.
Determine the location of the cargo longitudinal CG (see Figure 6-3)
Obtain the cargo moment:
Cargo Moment = Cargo Weight X Cargo CG
Perform weight and balance as previously described for passenger configura­
tion.
EXAMPLE II: Longitudinal CG Determination − Cargo
WEIGHT
(LB)
ITEM
Basic Weight (from Figure 6-4)
STATION
(ARM)
3272.8
MOMENT
(IN−LB)
688665
Pilot
170
130.7
22219
Copilot/Passenger
170
130.7
22219
Cargo
750
190.0
142500
1. Zero Fuel Weight
Add: Fuel (Jet-A)
4362.8
300.0
187.0
875603
56100
2. Gross Weight
4662.8
931703
Calculation of Longitudinal CG
CG at Zero Fuel Weight:
Moment at Zero Fuel Weight
Zero Fuel Weight
=
875603
4362.8
= 200.7
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
=
931703
4662.8
= 199.8
NOTE: The CG’s fall within the limits specified in Table Table 6−1; therefore, the loading
meets the longitudinal CG limits.
Reissue 3
Original
6−9
CSP−900RFM206A−1
Weight and
Balance Data
6−6.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PERMISSIBLE LATERAL LOADINGS − PASSENGER
CONFIGURATION
Safe operation of this helicopter requires that it be flown within established lateral
as well as longitudinal center of gravity limits.
It is therefore imperative that lateral center of gravity control be exercised.
All combinations of internal loadings are permissible if gross weight, longitudinal,
and lateral center of gravity considerations permit.
To determine the gross weight and center of gravity for a given flight are within
limits, proceed as follows.
Obtain the basic weight and longitudinal moment from The Basic Weight and Bal­
ance Record (Ref. Figure 6-4).
For pilot and passenger longitudinal and lateral center of gravity stations, see
Figure 6-2.
EXAMPLE III: Lateral CG Determination − Passenger
WEIGHT
(LB)
ITEM
Basic Weight (from Figure 6-4)
STATION
(ARM)
3272.8
MOMENT
(IN−LB)
1309
Pilot
170
+15.85
2695
Passenger - Rear Facing R/H
170
+19.00
3230
Passenger - FWD Facing R/H
170
+19.00
3230
--
10464
0
1. Zero Fuel Weight
Add: Fuel (Jet-A)
3782.8
500.0
2. Gross Weight
4282.8
10464
Calculation of Lateral CG
CG at Zero Fuel Weight:
Moment at Zero Fuel Weight
Zero Fuel Weight
=
10464
3782.8
= 2.77
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
=
10464
4282.8
= 2.44
NOTE: The CG’s fall outside the limits specified in Table Table 6−1; therefore, the
loading does not meet the lateral CG limits.
6−10
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
6−7.
CSP−900RFM206A−1
Weight and
Balance Data
LATERAL LOADING OF CARGO
To determine the gross weight and lateral center of gravity for a given flight are
with limits, proceed as follows.
Find weight of load.
Determine lateral location (station) of load center of gravity.
Measure load distance from aircraft (centerline) lateral station zero), right
(+) : left (-).
Obtain the lateral load moment as follows.
Lateral moment = weight X lateral station. (or use Table 6-10).
Perform weight and balance as previously described for longitudinal CG determina­
tions.
6−8.
INTERNAL LOADING OF CARGO
The following instructions should be followed when carrying internal cargo.
Restrain the cargo from shifting by using the correct number of tiedowns
in accordance with Table 6-4.
Locate restraint loops in accordance with Figure 6-6.
NOTE: Cargo carried in the baggage compartment shall not be higher than 36 inches.
To assure that cargo is properly secured, refer to Table 6-4.
The numbered tiedown location is located in the far left column of Table 6-4
with their respective restraint values in the six columns to the right.
Locate the cargo tiedown numbers for all of the tiedowns that you will be using
in the respective cargo areas (main cabin or baggage compartment).
Add the restraint values for each of the tiedowns in each of the three directions
(forward, left and right).
If the sum of restraint values in each of the three directions equals or exceeds the
weight of the cargo, then the cargo is sufficiently restrained.
NOTE: 1. Cargo should be centered in the cabin or baggage compartment.
2. Do not load cargo outside the perimeter defined by the cargo tiedown fittings.
Reissue 3
Original
6−11
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
EXAMPLE IV: Tiedown 500 pounds of cargo in the main cabin.
LATERAL
TIEDOWN No.
FORWARD
LEFT
RIGHT
1
---
220
---
14
2
--20
--40
220
---
13
20
---
40
4
11
130
130
40
---
--40
5
120
220
---
10
120
____
--____
220
____
TOTAL
540
520
520
Since all three values exceed the weight of the cargo (500 pounds), the cargo is
sufficiently restrained.
6−12
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Weight and
Balance Data
Table 6−4. Internal Cargo Loading
TIE-DOWN LOCATION
TIE-DOWN
NUMBER
RESTRAINT VALUE/POUNDS OF CARGO
MAIN CABIN
RESTRAINT DIRECTION
BAGGAGE COMPARTMENT
RESTRAINT DIRECTION
FUSELAGE
STATION
LATERAL
STATION
1
156.8
-27.0
2
174.9
-25.0
20
40
3
193.0
-25.0
130
20
4
211.1
-25.0
130
40
5
229.2
-27.0
120
220
6
229.2
-11.0
50
240
7
229.2
-8.0
50
240
8
229.2
8.0
50
240
9
229.2
11.0
50
240
10
229.2
27.0
120
220
11
211.1
25.0
130
40
12
193.0
25.0
130
20
13
174.9
25.0
20
40
14
156.8
27.0
220
15
156.8
11.0
240
16
156.8
8.0
240
17
156.8
-8.0
240
18
156.8
-11.0
240
19
232.9
-21.6
90
20
251.0
-24.8
120
21
233.3
0.0
22
257.9
0.0
23
232.9
21.6
90
24
251.0
24.8
120
25
230.5
-24.6
110
26
230.5
24.6
110
27
269.0
-17.5
105
28
269.0
17.5
105
FORWARD
LATERAL
LEFT (-)
LATERAL
RIGHT (+)
FORWARD
LATERAL
LEFT (-)
LATERAL
RIGHT (+)
220
185
135
20
110
85
85
120
120
185
135
Reissue 3
Original
110
6−13
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CARGO RESTRAINT LOCATION
1
18
17
16
15
14
2
13
FWD
3
12
LEFT
RIGHT
4
TIEDOWNS 25 AND 26 ARE ``D''
RINGS LOCATED AT WL 154.5
11
5
6
7
8
9
10
25
26
19
21
23
20
24
22
27
28
TIEDOWNS 19 THRU 28 ARE
``D'' RINGS. TIE DOWNS 27 AND
28 ARE LOCATED AT WL 155.0
Figure 6−6. Cargo Restraint
6−14
Reissue 3
Original
F90−036A
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Weight and
Balance Data
FUEL WEIGHT - POUNDS
1100
1075
1050
1025
1000
975
950
925
900
875
850
825
800
775
750
725
700
675
650
625
600
575
550
525
500
475
450
425
400
375
350
325
300
275
250
225
200
175
150
125
100
75
50
25
0
NOTES:
WEIGHTS AND MOMENTS BASED ON JET−A FUEL
(ASTM D−1655) AT 6.8 POUNDS PER U.S. GALLON
2. TOTAL WEIGHT OF FUEL IS DEPENDENT UPON
THE SPECIFIC GRAVITY AND TEMPERATURE
VARIATION SHOULD BE ANTICIPATED IN
GAUGE READINGS WHEN TANKS ARE FULL.
3. FUEL CG VARIES WITH QUANTITY
182
183
184
185
186
187
188
189
FUSELAGE STATION CG
190
191
192
F90−038A
Figure 6−7. Fuel Station Diagram − Jet−A
Reissue 3
Original
6−15
FUEL WEIGHT - POUNDS
CSP−900RFM206A−1
Weight and
Balance Data
1100
1075
1050
1025
1000
975
950
925
900
875
850
825
800
775
750
725
700
675
650
625
600
575
550
525
500
475
450
425
400
375
350
325
300
275
250
225
200
175
150
125
100
75
50
25
0
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NOTES:
WEIGHTS AND MOMENTS BASED ON JET B FUEL
(ASTM D−1655) AT 6.5 POUNDS PER U.S. GALLON
2. TOTAL WEIGHT OF FUEL IS DEPENDENT UPON
THE SPECIFIC GRAVITY AND TEMPERATURE
VARIATION SHOULD BE ANTICIPATED IN
GAUGE READINGS WHEN TANKS ARE FULL.
3. FUEL CG VARIES WITH QUANTITY
182
183
184
185
186
187
188
189
FUSELAGE STATION CG
Figure 6−8. Fuel Station Diagram − Jet−B
6−16
Reissue 3
Original
190
191
192
F90−037A
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Weight and
Balance Data
Table 6−5. Fuel Loading Table − Jet A (6.8 lb/U.S. gal)
VOLUME
U.S. GALLONS
WEIGHT
POUNDS
STATION
INCHES
MOMENT
IN−LBS
10
15
20
25
30
68
102
136
170
204
183.5
184.1
184.7
185.2
185.7
12478
18778
25119
31484
37883
35
40
45
50
55
238
272
306
340
374
186.2
186.7
187.1
187.4
187.7
44316
50777
57240
63716
70200
60
65
70
75
80
408
442
476
510
544
188.0
188.3
188.5
188.8
189.0
76704
83220
89736
96263
102800
85
90
95
100
105
578
612
646
680
714
189.2
189.4
189.6
189.8
189.9
109358
115913
122482
129030
135603
110
115
120
125
130
748
782
816
850
884
190.1
190.3
190.4
190.6
190.7
142195
148776
155366
161968
168579
135
140
145
150
155
160
918
952
986
1020
1054
1088
190.8
191.0
191.1
191.2
191.3
191.5
175173
181794
188425
195034
201672
208319
NOTES:
1. TOTAL WEIGHT OF FUEL IS DEPENDANT UPON THE SPECIFIC
GRAVITY AND TEMPERATURE. VARIATION SHOULD BE ANTICI−
PATED IN GAUGE READINGS WHEN TANKS ARE FULL.
2. FUEL CG VARIES WITH QUANTITY.
3. MAXIMUM USEABLE FUEL QUANTITY IS 994 LBS.
4. MAXIMUM USEABLE FUEL QUANTITY IS 1078 LBS. WITH RANGE
EXTENDER
Reissue 3
Original
6−17
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 6−6. Fuel Loading Table − Jet B (6.5 lb/U.S. gal)
VOLUME
U.S. GALLONS
WEIGHT
POUNDS
STATION
INCHES
MOMENT
IN−LBS
10
15
20
25
30
65
98
130
163
195
183.6
184.2
184.7
185.3
185.8
11934
17955
24007
30108
36225
35
40
45
50
55
228
260
293
325
358
186.2
186.7
187.0
187.4
187.7
42367
48537
54706
60889
67103
60
65
70
75
80
390
423
455
488
520
188.0
188.3
188.5
188.8
189.0
73320
79548
85786
92040
98280
85
90
95
100
105
553
585
618
650
683
189.2
189.4
189.6
189.8
190.0
104533
110811
117090
123370
129641
110
115
120
125
130
715
748
780
813
845
190.1
190.3
190.4
190.6
190.7
135929
142212
148512
154830
161142
135
140
145
150
155
160
878
910
943
975
1008
1040
190.9
191.0
191.1
191.2
191.4
191.5
167471
173792
180112
186449
192785
199129
NOTES:
1. TOTAL WEIGHT OF FUEL IS DEPENDANT UPON THE SPECIFIC
GRAVITY AND TEMPERATURE. VARIATION SHOULD BE ANTICIPATED
IN GAUGE READINGS WHEN TANKS ARE FULL.
2. FUEL CG VARIES WITH QUANTITY.
3. MAXIMUM USEABLE FUEL QUANTITY IS 950 LBS.
4. MAXIMUM USEABLE FUEL QUANTITY IS 1030 LBS. WITH RANGE
EXTENDER
6−18
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Weight and
Balance Data
Table 6−7. Weight and Longitudinal Moments − Pilot, Passengers, Baggage
PILOT OR
COPILOT/PASSENGER STA 130.7
REAR FACING
PASSENGER
STA 173.0
FWD FACING
PASSENGER
STA 213.0
MOMENT
(IN−LB)
MOMENT
(IN−LB)
MOMENT
(IN−LB)
100
13070
17300
21300
120
15684
20760
25560
140
18298
24220
29820
160
20912
27680
34080
180
23526
31140
38340
200
26140
34600
42600
220
28754
38060
46860
240
31368
41520
51120
PASSENGER
WEIGHT
(LBS)
BAGGAGE
(LBS)
AFT
BAGGAGE
STA 245.6
BAGGAGE
(LBS)
MOMENT
(IN−LB)
AFT
BAGGAGE
STA 245.6
MOMENT
(IN−LB)
100
24560
320
78592
120
29472
340
83504
140
34384
360
88416
160
39296
380
93328
180
44208
400
98240
200
49120
420
103152
220
54032
440
108064
240
58944
460
112976
260
63856
480
117888
280
68768
500
122800
300
73680
Reissue 3
Original
6−19
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 6−8. Weight and Longitudinal Moments − Cargo
WEIGHT
(LBS)
6−20
MOMENT (IN−LB)
STATION 160 STATION 180 STATION 200 STATION 220 STATION 240
100
16000
18000
20000
22000
24000
120
19200
21600
24000
26400
28800
140
22400
25200
28000
30800
33600
160
25600
28800
32000
35200
38400
180
28800
32400
36000
39600
43200
200
32000
36000
40000
44000
48000
220
35200
39600
44000
48400
52800
240
38400
43200
48000
52800
57600
260
41600
46800
52000
57200
62400
280
44800
50400
56000
61600
67200
300
48000
54000
60000
66000
72000
320
51200
57600
64000
70400
76800
340
54400
61200
68000
74800
81600
360
57600
64800
72000
79200
86400
380
60800
68400
76000
83600
91200
400
64000
72000
80000
88000
96000
420
67200
75600
84000
92400
100800
440
70400
79200
88000
96800
105600
460
73600
82800
92000
101200
110400
480
76800
86400
96000
105600
115200
500
80000
90000
100000
110000
120000
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Weight and
Balance Data
Table 6−9. Weight and Lateral Moments − Pilot and Passengers
PILOT OR
COPILOT/PASSENGER
STA. ±15.85*
REAR FACING
PASSENGER
STA. ±19.00*
FWD FACING
PASSENGER
STA. ±19.00*
MOMENT
(IN−LB)
MOMENT
(IN−LB)
MOMENT
(IN−LB)
100
110
1585
1744
1900
2090
1900
2090
120
1902
2280
2280
130
140
2061
2219
2470
2660
2470
2660
150
160
2378
2536
2850
3040
2850
3040
170
2695
3230
3230
180
2853
3420
3420
190
3012
3610
3610
200
3170
3800
3800
210
220
3329
3487
3990
4810
3990
4810
230
3646
4370
4370
240
3804
4560
4560
250
3963
4750
4750
260
270
4121
4280
4940
5130
4940
5130
280
4438
5320
5320
290
300
4597
4755
5510
5700
5510
5700
PASSENGER
WEIGHT
(LBS)
*Indicated moments are + (right lateral) and - (left lateral).
Reissue 3
Original
6−21
CSP−900RFM206A−1
Weight and
Balance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 6−10. Weight and Lateral Moments − Cargo
WEIGHT
(LBS)
MOMENT (IN−LB)
LATERAL
STATION ±5 in.*
LATERAL
LATERAL
LATERAL
STATION ±10 in.* STATION ±15 in.* STATION ±20 in.*
20
40
60
80
90
100
200
300
400
450
200
400
600
800
900
300
600
900
1200
1350
400
800
1200
1600
1800
100
110
120
130
140
500
550
600
650
700
1000
1100
1200
1300
1400
1500
1650
1800
1950
2100
2000
2200
2400
2600
2800
150
160
170
180
l90
750
800
850
900
950
1500
1600
1700
1800
1900
2250
2400
2550
2700
2850
3000
3200
3400
3600
3800
200
210
220
230
240
1000
1050
1100
1150
1200
2000
2100
2200
2300
2400
3000
3150
3300
3450
3600
4000
4200
4400
4600
4800
250
260
270
280
290
300
1250
1300
1350
1400
1450
1500
2500
2600
2700
2800
2900
3000
3750
3900
4050
4200
4350
4500
5000
5200
5400
5600
5800
6000
*Indicated moments are + (right lateral) and - (left lateral).
6−22
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
SECTION VII
SYSTEMS DESCRIPTION
TABLE OF CONTENTS
PARAGRAPH
PAGE
7-1. Helicopter Exterior Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-1
Figure 7-1. Helicopter - Major Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-2
7-2. Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-2. Door Opening Decals - Exterior . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-3
7-4
7-3. Tailboom and Empennage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-5
7-4. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-3. Landing Gear . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-6
7-7
7-5. Main Rotor System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-4. Main Rotor System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-8
7-9
7-6. Flight Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-5. Cyclic Controls Subsystem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-6. Collective Controls Subsystem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-7. Upper Flight Controls Subsystem . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-8. Anti-Torque Controls Subsystem (Sheet 1 of 3) . . . . . . . . . . . . . . . .
Figure 7-9. Anti-Torque Controls Subsystem (Sheet 2 of 3) . . . . . . . . . . . . . . . .
Figure 7-10. Anti-Torque Controls Subsystem (Sheet 3 of 3) . . . . . . . . . . . . . . .
Figure 7-11. VSCS Control Subsystem . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-10
7-12
7-13
7-14
7-15
7-16
7-17
7-18
7-7. Hydraulic Systems . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-12. Hydraulic System Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-13. Hydraulic System Block Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-14. Rotor Brake System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-19
7-20
7-21
7-22
7-8. Propulsion System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-15. Powerplant Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-16. Powerplant - Components . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-17. Drive System (Sheet 1 of 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-17. Drive System (Sheet 2 of 2) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-9. Engine Air Intake and Inlet Particle Separator (IPS) . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-18. Engine Air Inlet Screen/Inlet Particle Separator . . . . . . . . . . . . . .
7-23
7-23
7-24
7-25
7-26
7-27
7-28
7-10. Engine Power Management System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-28
Reissue 3
Original
7−i
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PAGE
PARAGRAPH
7-11. Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-30
Figure 7-19. IIDS Fuel System Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-31
Figure 7-20. Fuel System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-32
7-12. Electrical System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-21. Battery Power, External Power, and
DC Power Component Locator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-22. Battery Power and External Power Subsystem Block Diagram .
7-33
7-34
7-13. Environmental Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-23. Heat/Defog System Schematic . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-35
7-36
7-14. Integrated Instrumentation Display System (IIDS) . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-24. IIDS System Monitoring . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-25. IIDS Display Brightness Control . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-26. Alphanumeric Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 7-1. Automatic Alphanumeric Display
Warning/Caution/Advisory Messages . . . . . . . . . . . . . . . . . . . . . . . .
7-37
7-38
7-41
7-43
7-15. IIDS Data Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-45
7-16. Balance Monitoring System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-27. Balance Monitoring System Installation . . . . . . . . . . . . . . . . . . . . .
7-48
7-48
7-17. IIDS Menu Structures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-28. IIDS Top Level Menus . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-29. Time Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-30. Balance Monitor, Main Rotor Balance . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-31. Balance Monitor, Run M/R Measurements . . . . . . . . . . . . . . . . . . .
Figure 7-32. Balance Monitor, Main Rotor Configuration . . . . . . . . . . . . . . . . . .
Figure 7-33. Balance Monitor, Main Rotor Solution Options . . . . . . . . . . . . . . .
Figure 7-34. Balance Monitor, Display M/R Solution . . . . . . . . . . . . . . . . . . . . . .
Figure 7-35. Balance Monitor, M/R Track . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-36. Balance Monitor, NOTAR® Balance . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-37. Balance Monitor, NOTAR® Data . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-38. Balance Monitor, Spectrum . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-39. Balance Monitor, BMS Fault Log . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-40. Balance Monitor, BMS Version Log . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-41. Balance Monitor, BMS Maintenance . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-42. Aircraft Monitor, Exceedance Log Menu . . . . . . . . . . . . . . . . . . . . .
Figure 7-43. Aircraft Monitor - Trend Log . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 7-44. Aircraft Monitor, Fault Log Menu . . . . . . . . . . . . . . . . . . . . . . . . . . .
7-49
7-49
7-50
7-51
7-52
7-53
7-54
7-55
7-56
7-57
7-58
7-59
7-60
7-61
7-62
7-63
7-64
7-65
7−ii
Reissue 3
Original
7-33
7-43
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
PAGE
PARAGRAPH
Figure 7-45. Aircraft Monitor - IIDS Setup . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-66
Figure 7-46. Fuel Calibration . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-67
Figure 7-47. Set Engine Parameters . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-68
Figure 7-48. Set Time/Date . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7-68
Reissue 3
Original
7−iii
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
7−iv
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
SECTION VII
SYSTEMS DESCRIPTION
7−1.
HELICOPTER EXTERIOR DESCRIPTION
Design features:
Cockpit with outstanding field of view
All composite fuselage with expanded aluminium foil embedded in skin for light­
ning protection
Wide (52 inch), sliding cabin doors for loading bulky cargo
Crash resistant fuel cell
Built-in steps and work platforms for maintenance
NOTAR anti-torque system
H-type empennage with twin vertical stabilizers
Five-bladed main rotor with swept blade tips
Hingeless low drag main rotor hub
Optional engine inlet air particle separator
On-board systems monitoring and computerized track and balance
The patented NOTAR anti-torque system provides many benefits. It results in
low noise by locating the fan in the fuselage and eliminating the conventional noisy
tail rotor, provides outstanding safety because there is no exposed tail rotor, and
improved directional controllability over that of the conventional tail rotor helicopter.
The five-bladed main rotor is designed for outstanding performance and flying quali­
ties. Vibration in the passenger spaces is minimized by the incorporation of the
five blades and the unique dynamically-tuned ``static mount” that supports the
rotor and transmission. The swept tips on rotor blades improve performance and
reduce main rotor noise. Interior noise is minimized by using an acoustic noise
attenuating support for the transmission gearbox, and acoustic insulation in the
ceiling and sidewalls of the cabin.
Reissue 3
Original
7−1
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
MAIN ROTOR BLADE
ASSEMBLY
EMPENNAGE
ASSEMBLY
ENGINE
RIGHT
HAND
UPPER COWLING
AND FAIRINGS
CABIN DOOR
TRANSMISSION
ASSEMBLY
ENGINE
LEFT HAND
TAILBOOM
ASSEMBLY
ANTI-TORQUE
THRUSTER
FUSELAGE STRUCTURE
ASSEMBLY
COCKPIT
DOOR
BAGGAGE
COMPARTMENT
DOOR
ANTI-TORQUE
ASSEMBLY
COCKPIT
DOOR
CABIN DOOR
LANDING GEAR
ASSEMBLY
FLIGHT
CONTROLS
Figure 7−1. Helicopter − Major Components
7−2
Reissue 3
Original
F90−039A
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
The composite flexbeam main rotor hub replaces the normal hinges with a fiberglass/
epoxy flexbeam that twists and bends to accommodate the blade motions. It, and
the elastomeric lead/lag dampers, are located within the elliptical pitchcase for a
low drag hub that is composed of a minimum number of parts.
The empennage includes a fixed horizontal stabilizer and two controlled vertical
stabilizers that provide directional stability.
The engine inlets are flush in the sides of the cowling for an efficient, short air
path into the engine. They incorporate centrifugal-vortex type inlet particle separa­
tor (IPS) (optional) panels for protection from dust and debris. The IPS have automat­
ic bypass doors that open if the inlet becomes clogged.
The screened NOTAR inlet is on the top of the cowling, between the engines and
aft of the rotor. In this location it is protected from dust and debris, and is shaped
to direct NOTAR fan noise up and away from observers on the ground, thus helping
to minimize noise.
The cabin floor is approximately three feet above the ground. This provides space
under the fuselage for the energy absorbing landing gear to deflect, and room in
the lower fuselage for the 149 gallon fuel cell. A convenience step is provided on
the right side of the fuselage for entering and departing.
Step/handholds and fold-out work platforms are built into the sides of the fuselage,
forward and aft of the cabin doors, for easy access to equipment located on the
engine and transmission decks.
Two tiedown fittings are positioned high on the sides of the fuselage in line with
the forward edge of the cabin doors, and one on the fuselage centerline just above
the baggage compartment door. Fabric socks are used to capture the blade tips
for tying them to the landing gear crosstubes.
7−2.
FUSELAGE
The fuselage contains the cockpit; cabin; baggage compartment; fuel cell; NOTAR
fan, support, and ducts; and avionics equipment. The rotor/transmission support,
engines, and systems equipment are mounted on the top, and the landing gear
on the bottom. The fuselage structure has an aluminum upper deck, main frames,
and anti-plowbeams under the cockpit, with graphite/epoxy skins, keel beams,
cockpit framing, floors, and doors.
The fuselage is one of three components that contribute to an integrated systems
approach to the MD Explorer's hard landing energy absorbing concept. The others
are the landing gear and crew/passenger seats. This approach has served well in
the OH-6A, AH-64A, and MD500 helicopters.
The cabin has an open flat floor from the front of the copilot's station through
the cabin and to the back of the baggage compartment area. With the seats removed,
the entire floor area is usable for loading cargo.
Reissue 3
Original
7−3
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Space is provided in the nose for the battery; under the cockpit floor and in the
baggage compartment for avionics equipment; and under the baggage compartment
floor for air conditioning equipment. The single fuel cell is mounted in the belly
of the fuselage surrounded by bulkheads fore and aft, and keel beams to the sides.
Entry Doors:
Hinged cockpit doors, sliding cabin doors, and a hinged baggage compartment door
provide access. The cockpit doors have door release handles that allow the doors
to be removed (Ref. Section VIII). The windows in the cabin doors are easily remov­
able and the meet Transport Category emergency exit size criteria.
The cockpit door handles have four positions and main cabin door handles have
three positions:
COCKPIT DOOR OPENING DECAL
CABIN DOOR OPENING DECAL
SAFELOCK
SAFELOCK
OPEN
SLAM
OPEN
KEY
LOCK
SLIDING
LOCK
DOOR
F90−082
Figure 7−2. Door Opening Decals − Exterior
The rotor/transmission mount consists of an eight-legged metal truss that sup­
ports the mast base and the static mast. The transmission gearbox mounts beneath
the mast base and the rotor turns on the static mast tube on a set of tapered roller
thrust bearings. Two of the truss tubes on the right side of the aircraft are removable
for transmission maintenance.
Graphite/epoxy cowlings and access doors on top of the fuselage enclose the equip­
ment located there.
Saddle mounts in the lower fuselage clamp the forward and aft landing gear cross­
tubes in place.
Lightning protection for the graphite/epoxy skins is provided by expanded alumi­
num foil molded into the surface, with all components electrically bonded together.
Electromagnetic pulse protection (EMP) is provided by the aluminum structure,
the expanded aluminum foil on the graphite skins, and the shielding of individual
electric/avionics systems components and wiring.
7−4
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−3.
CSP−900RFM206A−1
Systems Description
TAILBOOM AND EMPENNAGE
Anti-torque, directional control, and yaw stability is provided by the NOTAR
fan, circulation control tailboom, the direct jet thruster, and the horizontal and
vertical stabilizers with VSCS.
The NOTAR fan is driven directly from the main transmission. The fan is located
in the aft fuselage, and supplies pressurized air to the tailboom (pressure ratio
= 1.02 to 1.12). Its blade pitch and the thruster nozzle rotational positions are oper­
ated by the anti-torque pedals.
The circulation control tailboom is a hollow graphite/epoxy cylinder that bolts
to the aft end of the fuselage and supports the horizontal and vertical stabilizers,
tail bumper, and the thruster. The tailboom directs the pressurized air to the thruster
while allowing some air to flow out of the two slots along its right side. This arrange­
ment creates a significant side force on the tailboom as a result of the circulation
flow around the tailboom while it is immersed in the main rotor downwash. The
remainder of the side force required for directional control is produced by airflow
out of the controllable direct jet thruster at the end of the tailboom.
The empennage consists of the horizontal stabilizer with upper and lower moveable
vertical stabilizers located at each tip. The horizontal and vertical surfaces are graph­
ite/epoxy. The horizontal stabilizer has an inverted NACA 2412 airfoil with a fixed
incidence of -1 degree. A trailing edge Gurney tab is installed above and below
the airfoil to balance aerodynamic moments. The vertical stabilizers have a hybrid
NACA 23012/NACA 0012 airfoil cambered toward the right side of the helicopter.
The vertical stabilizers are controlled in incidence by electro-mechanical actuators
located within the horizontal stabilizer that operate in response to collective pitch
inputs. Both vertical stabilizers also respond to the Vertical Stabilizer Control Sys­
tem (VSCS) to function as a yaw damper.
To minimize tail vibration, the horizontal stabilizer attaches to the top of the tailboom
with an energy absorbing mount that is hinged along a fore-and-aft axis at the
right side, and connected by an elastomeric damper on the left side.
Lightning protection is provided by a strip of aluminum foil bonded onto the
surface of the tailboom, expanded aluminum foil co-cured onto the empennage sur­
faces, and jumpers to form a continuous electrical path to the fuselage.
Reissue 3
Original
7−5
CSP−900RFM206A−1
Systems Description
7−4.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
LANDING GEAR
The landing gear (Figure 7-3) supports the helicopter when it is in contact with
the ground. The landing gear can withstand loads encountered during landing,
ground handling, and provides a stable platform to prevent ground resonance.
The landing gear primarily absorbs normal landing forces, with the capabilities
to absorb severe landing forces during overload conditions. The landing gear dimen­
sions are based on the required minimum roll-over and minimum pitch-over angles.
A minimum angle of 27 degrees is maintained from the center of gravity (CG) location
to the skid-to-ground contact point. The landing gear consists of the following compo­
nents:
Forward and Aft Crosstubes - Provide energy absorbing capabilities during nor­
mal or severe landings.
Forward and Aft Saddle Assemblies - Provide a means to attach the crosstube
assemblies to the fuselage attachment points.
Side Stop Clamp Assemblies - Prevent side movement of the crosstube assemblies.
Forward Spacer Fittings - Forward attachments for the skid tubes and forward
crosstube assembly.
Skid Tubes - Provide landing gear-to-ground contact points.
Damper Assemblies - Aft attachments for the skid tubes and aft crosstube assem­
bly.
Each damper has a reservoir fluid level indicator that is a rotating shaft which
shows through a 120 pie shaped window. When the reservoir is filled, the window
shows green with a very thin wedge of red showing to the first notch on the
housing. The thin wedge of red shows the reservoir is not completely full, to
allow for fluid expansion.
Ensure fluid level in reservoir is within limits.
Reservoir is near empty, when the window shows red and should be serviced
(RMM. Section 12-00-00).
7−6
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Systems Description
SIDE STOP
CLAMP ASSEMBLY
AFT
CROSSTUBE
PLUG
AFT
ABRASION STRIP
AFT
SADDLE ASSEMBLY
DAMPER
ASSEMBLY
FORWARD
CROSSTUBE
FORWARD
ABRASION STRIP
FORWARD
SPACER FITTING
FORWARD
SADDLE ASSEMBLY
STEP
SKID TUBE
GROUND HANDLING
ATTACH POINTS
MID ABRASION
STRIP
LANDING GEAR DAMPER
RESERVOIR FLUID
LEVEL INDICATOR
SECOND NOTCH
FIRST NOTCH
RED
GREEN
EMPTY
FULL
RESERVOIR INDICATOR CLOCKING TYPICAL
F90−045
Figure 7−3. Landing Gear
Reissue 3
Original
7−7
CSP−900RFM206A−1
Systems Description
7−5.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
MAIN ROTOR SYSTEM
The main rotor has five-blades and a hingeless flexbeam suspension system. The
rotor diameter is 33.83 feet with a blade chord of 10 inches. At its nominal 100
percent rotational speed (NR), the rotor turns at 392 rpm (695 feet/second tip speed).
The flexbeam is primarily a unidirectional fiberglass/epoxy, y-shaped member that
connects the blade to the rotor hub, and twists and bends to accommodate the blade
motions, resisting centrifugal force while transmitting drive torque to the blade.
The five flexbeams attach to the hub by five bolts.
The pitchcase is a hollow, elliptically shaped graphite/epoxy tube that surrounds
the flexbeam and is attached to both the flexbeam and the blade at its outboard
end by a pair of expandable-bushing bolts. The pitchcase provides flapwise, chord­
wise, and torsional stiffness to the inboard end of the blade and serves to transmit
the feathering control motions to the blade. The pitchcase is attached to the hub
at its inboard end by the elastomeric snubber/damper that provides centering for
flapping and feathering motions, and by a combination spring/damper restraint
for chordwise motion to eliminate ground resonance. An elastomeric bumper is
bonded to the flexbeam halfway along its length to bear against the inside of the
pitchcase and restrict a flexbeam bending oscillation that would otherwise occur
during spin-up and shut-down of the rotor.
7−8
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
ROTOR BLADE
ROTOR BLADE
RETENTION BOLTS
PITCHCASE
DRIVE
PLATE
FLEXBEAM
BUMPER
DAMPER
MAIN
ROTOR
HUB
FLEXBEAM
CENTERING
BEARING
PITCH CHANGE
HORN
UPPER
HUB
INBOARD
ABRASION STRIP
LOWER
HUB
DRIVE
RING
OUTBOARD
ABRASION STRIP
SCISSORS
TRIM TAB
ASSEMBLY
F90−046
Figure 7−4. Main Rotor System
The hub consists of two machined aluminum plates with a steel spacer between
them. The plates are grooved to accept the flexbeams and are bolted together with
the same bolts that attach the flexbeams. The hub mounts to the static mast by
a pair of grease lubricated, tapered roller bearings. A splined drive plate bolts to
the top of the hub and is driven by the main rotor shaft that rotates inside the
mast.
This static mast rotor support configuration has been used successfully in the
OH-6A, AH-64A, and MD500 helicopters and is incorporated into the MD Explorer
for three reasons:
Vibration Control - fuselage/mast/rotor structure is tuned dynamically for mini­
mum vibration.
Reduced transmission weight - gearcase is not required to support rotor loads.
Reissue 3
Original
7−9
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Safety - if the drive shaft should break, the rotor remains mounted to the mast
by its two bearings for a safe autorotation landing.
The main rotor blade is made from fiberglass/epoxy with a hollow leading edge
spar and a Nomex honeycomb-filled trailing edge. It has a theoretical twist of -10
degrees; and the high performance airfoil tapers in thickness from 12 percent at
it's inboard end to 9.5 percent at the tip. The outboard 14 inches of the blade planform
has a parabolic swept back taper. A 8 inch long by 3/4 inch chord trim tab is centered
on the 77 percent radius station. Two pockets in the bottom of the blade near the
tip are provided for installing blade balance weights.
A titanium abrasion strip protects the inboard, constant-chord portion of the blade
while an electroformed nickel abrasion strip is fitted outboard. A polyurethane sheet
protects the under side of the blade outboard.
The MD Explorer has a built-in track and balance system for the main rotor and
for the NOTAR fan blades that operates through the Integrated Instrument Display
System (IIDS).
Lightning protection is afforded by a continuous electrical path from blade tip
to rotor mast, and so on into the fuselage. This consists of the metal abrasion strip
on the blade, expanded aluminum foil co-cured onto the surface of the pitchcase,
dual jumpers across all joints, and twin carbon brushes for hub-to-mast continuity.
7−6.
FLIGHT CONTROLS
The flight controls provide a means of controlling blade pitch of the main rotor
in flight and during ground operations. The helicopter may be equipped with either
single or dual pilot configurations. The copilot's controls may be removed with the
use of quick disconnect fittings, when only single controls are used or required.
Cover plates are put over the holes in the floor or the disengaged pedals to prevent
objects or debris from entering these areas.
The flight controls integrate pilot inputs from the cyclic, collective, and anti-torque
subsystems. The cyclic and collective control stick inputs are mechanically linked
to the upper flight controls for longitudinal, lateral, and vertical control. The antitorque pedal inputs are transmitted to the NOTAR fan and direct jet thruster
for directional control. The flight controls consist of the cyclic controls, collective
controls, upper flight controls, anti-torque controls, and vertical stabilizer control
subsystems.
The cyclic controls subsystem controls helicopter pitch and roll attitudes (longitu­
dinal and lateral control). The cyclic controls move the upper flight controls to cycle
increases or decreases in the rotor blades angle of attack in a cyclic manner around
the rotor azimuth. The result is a change in the helicopter pitch and/or roll attitude.
The cyclic control subsystem consists of the following components:
Cyclic stick assembly - Provides pilot control of helicopter pitch and/or roll atti­
tude. This cyclic stick mount places the stick grip at its highest point above
7−10
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
the floor when it is farthest aft - it moves down as it moves forward. This allows
the pilot to rest his/her forearm on his/her thigh throughout all flight modes
for very comfortable flying.
Longitudinal and lateral trim actuators - Allow the pilot to position the cyclic
as required during flight and while on the ground.
Longitudinal linkages - Allow for cyclic input to the main rotor blades for helicop­
ter pitch control.
Longitudinal servoactuator - Hydraulically transfers longitudinal linkage inputs
to position the upper flight controls.
Lateral linkages - Allow for cyclic input to the main rotor blades for helicopter
roll control.
Lateral servoactuator - Hydraulically transfers lateral linkage inputs to position
the upper flight controls.
The collective controls subsystem controls helicopter lift (vertical control) and
thrust. As the collective stick assembly is moved, control linkages increase or de­
crease the rotor blades angle of attack.
The collective pitch system includes two automatic control features:
Conventional ``anticipatory” circuit into the Engine Electronic Controls (EEC) to
prepare them for an upcoming change of power demanded by the changing collective
pitch position, and vertical stabilizer incidence angle change (VSCS).
The collective control subsystem consists of:
Collective stick assembly - Provides pilot control of helicopter lift.
Collective friction unit - Allows collective stick assembly resistance to vary
from 5-25 pounds.
Collective friction release switch - Allows the pilot to release collective stick
assembly resistance.
Collective linkages - Allows the pilot to transmit collective input to the upper
flight controls.
Collective servoactuator - Hydraulically transfers collective linkage inputs to
the upper flight controls.
Reissue 3
Original
7−11
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
REF
UPPER DECK
LATERAL
CONTROL
ROD
ASSEMBLY
LONGITUDINAL CLOSET­
CONTROL ROD ASSEMBLY
CYCLIC STICK
ASSEMBLY
DUAL
LONGITUDINAL
CONTROL ROD
ASSEMBLY
LONGITUDINAL
BRACKET ASSEMBLY
CYCLIC CONTROL
STICK BOOT
EXPANDABLE
DIAMETER
BOLT ASSEMBLY
CYCLIC BASE
ASSEMBLY
LONGITUDINAL
BELLCRANK
ASSEMBLY
LATERAL CONTROLS
BRACKET ASSEMBLY
AFT COCKPIT
LONGITUDINAL
CONTROL ROD
ASSEMBLY
LATERAL
BRACKET
ASSEMBLY
LATERAL
BELLCRANK
ASSEMBLY
LATERAL
CONTROLS
CONTROL ROD
ASSEMBLY
LONGITUDINAL GRADIENT
SPRING ASSEMBLY
LONGITUDINAL TRIM ACTUATOR
CRANK ASSEMBLY
LATERAL GRADIENT
SPRING ASSEMBLY
COCKPIT LATERAL CONTROLS
TUBE ASSEMBLY
DUAL LATERAL ROD END
BALL BEARING
LONGITUDINAL CONTROLS
CONTROL ROD
ASSEMBLY
LATERAL
BELLCRANK
LATERAL TRIM ACTUATOR
LONGITUDINAL
ASSEMBLY
CRANK ASSEMBLY
TRIM ACTUATOR ASSEMBLY
LATERAL
TRIM ACTUATOR
F90−047−1
Figure 7−5. Cyclic Controls Subsystem
7−12
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Systems Description
COLLECTIVE HYDRAULIC
SERVOACTUATOR
LONGITUDINAL/
COLLECTIVE
FOD COVER
UPPER DECK
COLLECTIVE CONTROL
ROD ASSEMBLY
CONTROL BRACKET
ASSEMBLY
COLLECTIVE
BELLCRANK ASSEMBLY
COLLECTIVE
BRACKET ASSEMBLY
COLLECTIVE
CONTROL ROD ASSEMBLY
DETENT MODULE
ASSEMBLY
COLLECTIVE
BELLCRANK ASSEMBLY
COLLECTIVE CONTROL
ROD ASSEMBLY
SENSOR
LINK ASSEMBLY
DETENT MODULE
MOUNTING BRACKET
PILOT
COLLECTIVE STICK
ASSEMBLY
SENSOR COLLECTIVE
POSITION BELLCRANK
ASSEMBLY
POTENTIOMETER
CLAMP
POTENTIOMETERS
SENSOR
BRACKET
ASSEMBLY
COLLECTIVE FRICTION
RELEASE SWITCH
INTERCONNECT
CABLE ASSEMBLY
COLLECTIVE
BELLCRANK ASSEMBLY
COLLECTIVE
CONTROL STICK BOOT
COPILOT
COLLECTIVE STICK ASSEMBLY
COLLECTIVE
FRICTION UNIT
COLLECTIVE
BRACKET ASSEMBLY
COLLECTIVE STICK
BRACKET ASSEMBLY
COLLECTIVE INTERCONNECT
CONTROL ROD ASSEMBLY
F90−047−2
Figure 7−6. Collective Controls Subsystem
Reissue 3
Original
7−13
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Main Rotor Controls:
The main rotor mechanical control system uses conventional pushrods and bell­
cranks under the cockpit floor; in the forward, right hand cockpit/cabin bulkhead;
and in the cabin ceiling to transmit the control motions to the dual tandem hydraulic
actuators that operate the rotor control mixer and the swashplate.
SCISSORS DRIVE
LINK ASSEMBLY
ROTOR CONTROL
PITCH LINK ASSEMBLY
SWASHPLATE
ASSEMBLY
LATERAL ANTI-TORQUE
DRIVE LINK ASSEMBLY
COLLECTIVE DRIVE
LINK ASSEMBLY
MIXER
ASSEMBLY
F90−047−3
Figure 7−7. Upper Flight Controls Subsystem
Anti-torque Controls:
The anti-torque pedals are adjustable fore and aft and include an adjustable friction
device. They operate through a pushrod/bellcrank system and a single hydraulic
actuator to control the rotation of the direct jet thruster and change the blade pitch
angle of the NOTAR fan to maintain constant air pressure in the tail boom as
the thruster nozzle opens and closes. The hydraulic actuator operates the NOTAR
fan blade pitch through a pushrod/bellcrank/cam linkage, and the thruster rotation
through a push/pull type cable along the length of the tailboom and a local tension
cable loop at the thruster. The pedals do not control the vertical stabilizers.
7−14
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
DIRECTIONAL
CONTROL ROD ASSEMBLY
HEEL REST
ASSEMBLY
CSP−900RFM206A−1
Systems Description
REF UPPER DECK
DIRECTIONAL
BELLCRANK ASSEMBLY
LOWER CLOSET
DIRECTIONAL
BELLCRANK ASSEMBLY
AFT DIRECTIONAL
CONTROL ROD ASSEMBLY
PEDAL
ADJUSTMENT
HANDLE
COPILOT DUAL CONTROL
DIRECTIONAL PEDAL ASSEMBLY
PEDAL
CRANK
ASSEMBLY
HEEL REST
ASSEMBLY
PILOT DUAL CONTROL
DIRECTIONAL
PEDAL ASSEMBLY
RIGHT
HEEL REST
SUPPORT
DIRECTIONAL
INTERCONNECT
CONTROL ROD ASSEMBLY
LEFT
HEEL REST
SUPPORT
DIRECTIONAL PEDAL
LINK ASSEMBLY
F90−047−4
Figure 7−8. Anti−Torque Controls Subsystem (Sheet 1 of 3)
Reissue 3
Original
7−15
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SPLITTER
ASSEMBLY
FOD
COVER UPPER
DIRECTIONAL
DECK
BELLCRANK
ASSEMBLY
DIRECTIONAL
BRACKET ASSEMBLY
ANTI-TORQUE
SERVO ACTUATOR
DIRECTIONAL
CONTROL ROD
ASSEMBLY
DIRECTIONAL
CONTROL ROD
ASSEMBLY
NOTAR® FAN INPUT FORCE
LIMITING CONTROL ROD
DIRECTIONAL CONTROLS
CONTROL ROD
ASSEMBLY
DIRECTIONAL
CONTROL ROD
ASSEMBLY
DIRECTIONAL
BRACKET ASSEMBLY
DIRECTIONAL
BELLCRANK
ASSEMBLY
CONTROL
BRACKET ASSEMBLY
NOTAR® FAN INPUT FORCE
LIMITING CONTROL ROD
ASSEMBLY
DIRECTIONAL
BRACKET
ASSEMBLY
DIRECTIONAL CABLE
ATTACH BRACKET
TO THRUSTER
CONTROL
OUTER BELLCRANK
ASSEMBLY
DIRECTIONAL
BELLCRANK
ASSEMBLY
NOTAR® FAN
LINKAGE
INNER BELLCRANK
ASSEMBLY
DIRECTIONAL
CONTROL CABLE
ASSEMBLY
DIVERTER
PLATE ASSEMBLY
DIRECTIONAL CONTROLS
CONTROL ROD ASSEMBLY
F90−047−5A
Figure 7−9. Anti−Torque Controls Subsystem (Sheet 2 of 3)
7−16
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Systems Description
ROTATING CONE
ASSEMBLY
THRUSTER BUILDUP
ASSEMBLY
TAILBOOM
ASSEMBLY
THRUSTER CONTROL
ROD ASSEMBLY
DIRECTIONAL CONTROL
CABLE ASSEMBLY
THRUSTER CONTROL
ROD ASSEMBLY
AFT
THRUSTER CONTROL
CABLE ASSEMBLY
THRUSTER
STATIONARY
CONE ASSEMBLY
THRUSTER CONTROL
SECTOR ASSEMBLY
THRUSTER CONTROL
DRUM ASSEMBLY
VIEW ROTATED
THRUSTER DRUM
BRACKET ASSEMBLY
F90−047−6
Figure 7−10. Anti−Torque Controls Subsystem (Sheet 3 of 3)
Reissue 3
Original
7−17
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
The Vertical Stabilizer Control System (VSCS) operates the incidence of the
vertical stabilizers through two electro-mechanical actuators, one for the left stabi­
lizer and one for the right stabilizer. One portion of the system is a fly-by-wire
actuator of stabilizer incidence as a function of collective pitch stick position. It's
purpose is to provide an anticipation that a power change is occurring to prevent
rotor droop and to maximize the anti-torque contribution of the stabilizers at high
speed thereby minimizing power required by the fan - leaving more power available
for the main rotor. The second portion of the system is a fly-by-wire yaw damping
function that uses yaw gyro/lateral accelerometer signals to impose a supplementary
incidence on both vertical stabilizers. Instrumentation/control includes a dual indica­
tor on the instrument panel to show incidence angle of the two vertical stabilizers;
a LEFT STAB FAIL, RIGHT STAB FAIL, or TOTAL STAB FAIL yellow CAUTION
annunciator on the IIDS alphanumeric display; two OFF/ON/TEST ``L VSCS R''
switches on the utility panel, and a VSCS Synchronization switch located on the
collective control module (Ref. Section IV). The VSCS Synchronization switch allows
the pilot to reset the VSCS to operate around the current lateral acceleration and
yaw rate. This feature is useful when transitioning from hovering to forward flight,
and when transitioning from a turn to level flight or from level flight into a turn.
L
VERTICAL STAB
R
L
VERTICAL STAB
R
VSCS INDICATOR
RIGHT
VERTICAL
STABILIZER
RIGHT VERTICAL
STABILIZER LINKAGES
YAW
RATE
GYRO
LATERAL
ACCELEROMETER
RIGHT VSCS
CONTROL UNIT
RIGHT LINEAR
ACTUATOR
COLLECTIVE
CONTROL POSITION
TRANSDUCERS
YAW RATE
GYRO
LEFT
LINEAR
ACTUATOR
LEFT
VERTICAL
STABILIZER
LEFT VERTICAL
STABILIZER LINKAGES
LEFT VSCS
CONTROL UNIT
F90−060A
Figure 7−11. VSCS Control Subsystem
7−18
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−7.
CSP−900RFM206A−1
Systems Description
HYDRAULIC SYSTEMS
Flight Controls:
The helicopter is equipped with two hydraulic systems for operation of the flight
controls. Under certain conditions, the main rotor control loads are such that they
require at least one hydraulic system operating at all times; hence, the dual system
for safety. However, the aircraft can be flown in a minimally degraded condition
with the anti-torque actuator depressurized.
The system is powered by two variable displacement hydraulic pumps mounted
on and driven by the main transmission, has a reservoir/manifold for each system
placed on opposite sides of the upper fuselage deck, and has three tandem actuators,
one for each cyclic pitch function and one for collective pitch of the main rotor.
The #1 system operates only the main rotor controls while the #2 system operates the
main rotor controls and also the NOTAR anti-torque control system.
The main rotor actuators are mounted forward of the main rotor while the antitorque actuator is mounted in the cabin ceiling just aft of the right hand cabin
door.
A hand pump option is installed for use in servicing the hydraulic systems in the
field.
The two systems normally operate at 500 psi each for a total system pressure of
1000 psi. If pressure in one system should drop to less than 400 psi, the other system
automatically compensates by increasing its pressure to maintain a total system
pressure of 1000 psi nominal. A yellow caution annunciator,
``1 HYD'' or ``HYD 2'', illuminates on the IIDS caution/warning display and a caution
message is displayed on the alphanumeric display when the affected system's pres­
sure falls below 250 psi.
Reissue 3
Original
7−19
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SYSTEM NO. 2
PUMP
SYSTEM NO. 2
MANIFOLD
SYSTEM NO. 1
PUMP
SYSTEM NO. 1
MANIFOLD
SAMPLING
VALVE
BLEED VALVE
GSE PANELS
TEMPERATURE
SWITCH
FLUID LEVEL
SIGHT GAUGE
FILTER BOWL
(RETURN)
PRESSURE
TRANSDUCER
FILTER BOWL
(PRESSURE)
MANIFOLD / RESERVOIR
CURRENT CONFIG
SYSTEM
SELECT
SOLENOID
F90−061A
Figure 7−12. Hydraulic System Installation
7−20
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
HAND
PUMP
(OPTIONAL)
SYSTEM 1
VARIABLE
DELIVERY
PUMP
GSE
PANEL
CSP−900RFM206A−1
Systems Description
SYSTEM 2
VARIABLE
DELIVERY
PUMP
MANIFOLD
RESERVOIR
MANIFOLD
RESERVOIR
GSE
PANEL
COLLECTIVE SERVO ACTUATOR
LONGITUDINAL SERVO ACTUATOR
LATERAL SERVO ACTUATOR
DIRECTIONAL SERVO ACTUATOR
F90−062A
Figure 7−13. Hydraulic System Block Diagram
Reissue 3
Original
7−21
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Rotor Brake:
A completely separate secondary stand-alone hydraulic system is a part of the
rotor brake installation. It incorporates a master cylinder operated by the brake
handle in the cockpit, and the actuator that operates the disc brake on the back
side of the transmission where the NOTAR drive shaft connects. A yellow
BRAKE caution annunciator in the IIDS secondary display screen warns if the
brake is not fully disengaged.
HYDRAULIC
TUBE
CONTROL LINKAGE
MASTER CYLINDER WITH
INTEGRAL RESERVOIR
BRAKE
CALIPER
F90−063
Figure 7−14. Rotor Brake System
7−22
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−8.
CSP−900RFM206A−1
Systems Description
PROPULSION SYSTEM
The propulsion system is designed to meet the engine isolation requirements for
multi-engine rotorcraft that are defined by the Category A requirements of FAR
Part 29, paragraph 29.903(b), as modified for Part 27 rotorcraft.
Powerplant:
This system consists of two Pratt and Whitney Canada (P&WC) PW206A turbo­
shaft engines mounted above the baggage compartment and pointing inboard
to drive into the main transmission gearbox (Ref. Figure 7-15 and Figure 7-16).
Each engine is mounted to the fuselage upper deck by a three point, adjustable
titanium mount. The air inlet which is in the middle of the engine is located
inside a titanium-walled inlet plenum that leads from a flush-mounted inlet
in the side of the cowling. The combuster end of the engine is surrounded by
titanium firewalls forward, aft, inboard side, and below. It is covered by a fairing
door, and is ventilated by an exhaust-driven ejector at the aft end of the compart­
ment.
FORWARD
FIRE SEAL
PRIMARY EXHAUST
NOZZLE ASSEMBLY
AFT
FIRE SEAL
SECONDARY
EJECTOR
INSULATION
BLANKET
TRIPOD
MOUNT
ENGINE
AIR INLET
REAR STAY
ASSEMBLY
TRIPOD
MOUNT
FWD INLET
PANEL
AFT INLET
PANEL
F90−064−1
Figure 7−15. Powerplant Installation
Reissue 3
Original
7−23
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TORQUE TRIM MODULE
FMU
FUEL MANIFOLD
T6 THERMOCOUPLE
FUEL PUMP
FUEL NOZZLE
FUEL FILTER
AIR INLET SCREEN
LH OIL LEVEL SIGHT GLASS
OIL FILTER COVER
OIL FILTER IMPENDING
BYPASS INDICATOR
CHIP DETECTOR
EGT TRIM MODULE
T1 SENSOR
NP SENSOR
T1/T6 TERMINAL BOX
NG SENSOR
PMA
STARTER GENERATOR PAD
RH OIL LEVEL SIGHT GLASS
FREON PUMP PAD
(IF INSTALLED - RH ENGINE ONLY)
OIL PRESSURE PORT
OIL TEMPERATURE PORT
TORQUE SENSOR
F90−064−2
Figure 7−16. Powerplant − Components
7−24
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
Drive system:
A short shaft with flexible diaphragm couplings and anti flail devices connects
each engine to the transmission. A longer shaft with similar couplings drives
the NOTAR fan. The main rotor drive shaft connects the planet gear carrier
in the top of the transmission to the main rotor hub through a splined connection
at each end. The engines and transmission are electrically bonded to the airframe
by suitable jumpers.
MAIN ROTOR
DRIVE SHAFT
STATIC MAST
SUPPORT ASSEMBLY
PRESSURE
TRANSDUCER
INPUT
DRIVE SHAFTS
STRUT
ASSEMBLY
BLOWER
HOUSING
ASSEMBLY
LUBRICATION
PUMP
TRANSMISSION
ASSEMBLY
DECK FITTING
ASSEMBLY
HYDRAULIC
PUMP DRIVE
TEMPERATURE
PROBE AND
SWITCH
F90−065−1
Figure 7−17. Drive System (Sheet 1 of 2)
Reissue 3
Original
7−25
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
To minimize structurally-transmitted acoustic noise from the transmission into
the passenger spaces, the transmission is supported from the mast base by eight
bolts in elastomeric bushings, and is restrained against rotation by a toothed coupling
arrangement that has a contoured elastomeric ring between the bottom of the mast
base and the top of the gearbox.
EXHAUST DUCT
INTERCONNECT DUCT
OIL COOLER
AIRFRAME
DECK
INLET DUCT
NOTAR FAN
DRIVE SHAFT
VIEW ROTATED
PRESSURE SWITCH
(LOW)
MAGNETIC
CHIP DETECTOR
F90−065−2
Figure 7−17. Drive System (Sheet 2 of 2)
Engine and transmission lubricating oil is cooled by air/oil heat exchangers
mounted in the sides of the cowling alongside the transmission. Each cooler is split
so that it serves separately one engine's requirements plus half of the transmission's
requirements. A direct drive fan on each side of the transmission induces ambient
air to flow through the cooler cores. Each engine has its own lubrication pump;
the transmission's pump is located low on the front centerline of the gearbox.
Magnetic chip detectors are provided for each engine and the transmission. The
detector in the transmission has ``burn-off '' capability; the detectors in the engines
do not.
7−26
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−9.
CSP−900RFM206A−1
Systems Description
ENGINE AIR INTAKE AND INLET PARTICLE SEPARATOR (IPS)
The air intake system provides a path for ambient air to enter each engine compressor
case inlet. The air intake system consists of an inlet screen or optional inlet particle
separator for each engine that prevents debris from entering the engine ducts.
Inlet screen:
The standard inlet screens are 1/4 inch steel wire mesh screens located on the
upper intake cowlings (Ref. Figure 7-18). Each engine inlet screen prevents large
foreign objects from entering the inlet plenum. A bypass opening is located at
the aft end of each inlet screen. The aft facing bypass opening assures airflow
if the screen becomes clogged.
IPS (if installed):
The inlet particle separator is an inertial type particle separator that removes
debris from the ambient air before it enters the engine. The particle separator
is located on the upper intake cowling (Ref. Figure 7-18). Ambient air enters
the particle separator and the air velocity is increased as the air passes over
swirl guides. The swirl guides create a vortex that separates heavy particles
from the air. The particles drop to the bottom of the particle separator panel.
A solenoid valve and bleed air lines route engine compressor bleed air to the
particle separator ejector to eject the particles overboard. The ejector is controlled
by the pilot through the IPS switch located on the Utility panel. In the event
that the particle separator becomes clogged with debris, solenoid operated bypass
doors automatically open for both engines inlets.
NACA inlet:
The NACA engine inlets provide ``ram air'' for enhanced engine operation/perfor­
mance during cruise flight. If the aircraft is equipped with an IPS, the NACA
inlets incorporate doors that open/close automatically when the airspeed is great­
er/less than 47 KIAS.
On aircraft with the standard engine inlet screen, the NACA inlet does not include
doors, but has a screen covering the inlet.
If the aircraft is equipped with an IPS, a NACA inlet switch is provided on the
options switch panel that allows the pilot to override the automatic door opening
feature and leave the NACA inlet doors in the closed position. NACA door position
indicator lights are located on the instrument panel below the VSCS indicators.
Additional information for operations with the NACA inlet may be found in Sec­
tions II, III, and IV.
Reissue 3
Original
7−27
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
STANDARD INLET SCREEN
NACA INLET
(IF INSTALLED)
BLEED AIR
TUBE ASSEMBLY
SOLENOID
SHUTOFF VALVE
EJECTOR
TUBE ASSEMBLY
PARTICLE SEPARATOR EJECTOR
PARTICLE
SEPARATOR PANEL
BYPASS DOOR
NACA INLET DOOR (IF
INSTALLED)
BYPASS DOOR
SOLENOID LATCH
F90−043A
Figure 7−18. Engine Air Inlet Screen/Inlet Particle Separator
7−10. ENGINE POWER MANAGEMENT SYSTEM
Automatic Engine Control:
The Pratt and Whitney PW206A engine is equipped with a single channel Full
Authority Digital Electronic Control (FADEC) which consists of an Electronic
Engine Control (EEC), Fuel Metering Unit (FMU), and fuel pumps. A manual
backup system is provided for emergency operation in case the EEC becomes
inoperative. The pilot's controls for normal operation consist of two rotary engine
control switches on the engine control panel for the left and right engines. These
switches are gated between OFF and IDLE: the switch knobs must be lifted
to pass the gates. The other switch positions are FLY and TRAIN and are not
gated. For normal operation, the two twist grips on the collective pitch stick
are always left in their NORMAL detent position.
7−28
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Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
The EEC's of the two engines are connected together electrically for a torquematching function, and are both connected electrically to the collective stick
position resolvers in the conventional power-anticipation mode.
When the EEC's are working properly, the procedure for starting and stopping
requires no more than selection of the desired engine operation with an engine
control switch.
P&WC has built into the PW206A engine the proper shielding to protect the
EEC's from the HIRF threat, and the helicopter's wiring system components
that are associated with the EEC's are protected in a similar manner. With this
protection in place, freedom from lightning damage is also assured.
Train Mode:
Placing an engine control switch in the TRAIN position will simulate a one engine
inoperative condition by resetting the selected engine's governed speed to 92
percent NP, thereby putting the engine on standby while allowing single engine
training on the opposite engine. In the event of an engine failure on the opposite
engine, the engine in TRAIN will automatically revert to 100% NP.
Emergency Manual Control:
The controls for manual operation of the engine power consist of two twist grips
on the collective pitch stick and two push buttons on the switch module at the
end of the collective stick.
The EEC is designed to ``fail-fixed” (EEC's stepper motor is fixed at its last con­
trolled power setting) so there is no sudden change in the level of power if an
EEC becomes inoperative. The only noticeable happening is illumination of the
yellow EEC/red FAIL warning on the Integrated Instrument Display System
(IIDS). No matter at what power level the EEC becomes inoperative, there is
sufficient travel in the twist grip to control the engine manually from full power
to idle and engine shutdown.
After the EEC becomes inoperative, the pilot uses the appropriate twist grip
on the collective stick to modulate the power.
Reissue 3
Original
7−29
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−11. FUEL SYSTEM
The fuel system is designed to the FAR Part 27 requirements plus the Category
A engine isolation general requirements of FAR Part 29, paragraph 29.903(b) as
modified for Part 27 rotorcraft.
The single crash-resistant elastomeric fuel cell is capable of holding 149 U.S. gallons
of jet fuel and is located in the lower fuselage under the main cabin floor. It is
contained between crash-resistant keelbeams and bulkheads, with a support panel
underneath.
The powerplant separation feature includes a partial-height baffle that runs fore
and aft along the bottom center of the cell to trap enough fuel on either side to
prevent simultaneous dual engine flameout if one side were punctured and the
cell lost all its fuel down to that retained on the undamaged side of the baffle. This
is a pressurized fuel system with a separate fuel pump located in the sump in each
side of the cell. Normally each pump supplies its own engine, but a crossflow valve
allows fuel distribution management.
The cell is designed with a seven percent expansion space, and has two anti-slosh
baffles across it. Pilot-operated shutoff valves are positioned at the engine firewalls.
Self‐closing breakaway fittings are installed where fuel lines penetrate the cell walls
and where they penetrate the engine deck. Overboard fuel cell vent lines incorporate
rollover valves and flame arrestors located in the vent system stand pipes.
The gravity-type fuel filler port is located on the right side of the fuselage just
aft of the pilot's cockpit door.
Two sump overboard drains for removing sediment and water (one for each side
of the cell) are operated by knobs located under the right side cabin step.
The engine fuel drain system provides a path for residual fuel from the combusters
and fuel control system that remains after shutdown to be directed overboard by
way of catch cans located under the baggage compartment floor.
A provision is made in the fitting at the aft left hand corner of the cell for making
a connection to an optional auxiliary fuel tank.
Another available option is a ``range extender” that allows carrying an additional
12 U.S. gallons of fuel.
7−30
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
The pilot controls the fuel system by the Fuel System panel mounted switches.
Fuel level is sensed by a forward probe and an aft probe, and is displayed on the
IIDS. Two fuel pressure switches activate caution lights in the IIDS when the pres­
sure falls below the acceptable limit.
FUEL
FUEL LOW WARNING
SEGMENT (RED)
FUEL QUANTITY
SEGMENTS (GREEN)
FUEL LOW CAUTION
SEGMENTS (YELLOW)
FUEL LOW WARNING TICK MARK (RED)
FUEL SHUTOFF VALVE POSITION
ANNUNCIATOR (YELLOW)
CURRENT FUEL QUANTITY
DIGITAL DISPLAY (WHITE)
FUEL FILTER IMPENDING
BYPASS ANNUNCIATOR (YELLOW)
FUEL FILTER IMPENDING
BYPASS ANNUNCIATOR (YELLOW)
LOW FUEL PRESSURE
ANNUNCIATORS (YELLOW)
LB
FUEL FLOW LINE
CROSS FEED VALVE POSITION
ANNUNCIATOR (YELLOW)
LOW FUEL PRESSURE
ANNUNCIATORS (YELLOW)
F90−114
Figure 7−19. IIDS Fuel System Display
Fuel quantity (FUEL) is shown by a vertical bargraph inside a fuel tank icon
rectangle, with the corresponding digit value in pounds, shown immediately below.
The green bar shortens vertically from the top as fuel is burned proportional to
the total tank volume. When the green box disappears, two yellow segments illumi­
nate below to indicate a low fuel caution (approximately 45 minute reserve). When
the last yellow segment disappears, a red segment illuminates below to indicate
low fuel (approximately 20 minute reserve). The red ``tick'' marks beside the red
segments are activated when the low level sensor reaches the warning level (97
to 117 lbs - 15 minutes fuel remaining).
NOTE: If the voltage for the probe drops below the specified operating limit, the
segments in the fuel quantity vertical scale blank with the digital quantity still
active.
Fuel flow to the engines is shown below the fuel quantity bargraph: Connections
from the fuel tank to each engine is shown immediately below the digit value of
Reissue 3
Original
7−31
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
fuel quantity. A solid line indicates normal fuel flow and alternating white and yellow
offset segments indicate low fuel pressure.
The display of fuel valve cross-feed and left and right engine fuel valve
position is shown by a segment block between the fuel lines for crossfeed and
a segment above and below each fuel line for the respective left and right fuel valves.
During the time a fuel valve is in transit between open and closed positions, the
fuel valve indications will flash. Fuel valve in transit is defined by both fuel valve
input discreets being open circuit.
The fuel filter impending bypass status is shown by an inverted ``U'' above each
fuel line indication.
FUEL SHUTOFF
VALVE (2)
RIGHT
ENGINE
VIEW LOOKING AFT
LEFT
ENGINE
ENGINE DECK FRANGIBLE
CONNECTOR (2)
FUEL PRESSURE
SWITCH (2)
INTERCONNECT FITTING
VAPOR SHROUD DRAIN (2)
(TO ENGINE DRAIN SYS)
TO FWD RH
VENT SYS
M
M
M
TO AFT LH
VENT SYS
FUEL CELL
BAFFLE (2)
RH FUEL
FEED SYS
FUEL FILLER
ASSY
RH
FUEL FEED
VAPOR SHROUD
VENT ROLLOVER
VALVE (4)
GRAVITY
FILL
VALVE
FLAME
ARRESTOR (2)
FWD LH
VENT SYS
CROSSFEED
VALVE
VAPOR SHROUD
OVRBD DRAIN
LH FUEL FEED
VAPOR
SHROUD
FUEL CELL
LH FUEL
FEED SYS
FUEL FEED
FRANGIBLE
CONNECTOR (2)
VENT OVBD
DRAIN (2)
SUMP DRAIN
CABLE
FUEL BOOST
PUMP (2)
CHECK VALVE
(2)
SUMP OVBD
DRAIN (2)
FUEL QTY PROBE 2 PL
LOW LEVEL INDICATOR
ON AFT PROBE
SUMP DRAIN
VALVE (2)
Figure 7−20. Fuel System Schematic
7−32
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FUEL CELL OUTLET
VAPOR SHROUD
DRAIN (2)
F90−040A
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
7−12. ELECTRICAL SYSTEM
The electric system is designed to maintain separation of the power generating sys­
tems. Wiring for each system is physically separated to each side of the helicopter to
the greatest extent possible. Power from the two generators does not pass together
through a single connector at any point on the aircraft to preclude any single point
failure that could result in loss of power to the essential bus.
Two engine-mounted starter-generators rated at 200 amperes each provide
29 volts DC to the aircraft. Bus tie relays provide redundancy by allowing either
generator to provide power to all busses.
The essential bus relay allows the essential bus to be powered by either of the
two generators, or by the battery if all power from the generators is lost.
Starter and generator functions are directed by individual generator control
units (GCU), each of which provides starter control, voltage regulation, and protec­
tive functions. Electric power is distributed by two electric busses and a battery
bus. A starter contactor connects the starter generator to the battery bus. After
a successful start, the starter-generator begins generating current and is brought
on line by the GCU through the generator contactor.
The pilot monitors generator load on the IIDS. The pilot can manually reset or dese­
lect either generator by using the generator switches located on the Electrical Master
panel.
A 22 ampere-hour nickel-cadmium battery is used for engine start and for
reserve electric power. The battery relay and external power relay are controlled
by the power switch on the Electrical Master panel.
STARTER/GEN
STARTER/GEN
GENERATOR CONTROL UNIT
EXTERNAL POWER
RECEPTACLE
BATTERY
GENERATOR CONTROL
UNIT
ELECTRICAL
LOAD CENTER
POWER AND L/R
GENERATOR SWITCHES
EXTERNAL POWER BOX
RELAY
F90−067
Figure 7−21. Battery Power, External Power, and DC Power Component Locator
Reissue 3
Original
7−33
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
The key switch is located on the right hand side of the instrument panel. All
switches and brightness controls that operate the electric system are on the console.
The ground power receptacle for 28 volts DC is in the right hand side of the fuselage
below and forward of the pilot's door. Two grounding jacks are located on the right
hand side of the fuselage, one adjacent to the ground power receptacle and one
adjacent to the fuel filler port.
Circuit breakers for essential circuits are located in the cockpit on the Essential
Bus panel; nonessential breakers are located in the baggage compartment ceiling.
One 29 volt DC outlet is located in the cockpit on the copilot's side of the console,
and another one is on the left hand cabin wall aft of the cabindoor.
EXTERNAL
POWER
RECEPTACLE
TO IIDS
EXTERNAL
POWER
RELAY
TO DISTRIBUTION
BATTERY
BUS
TO IIDS
TO IIDS
BATT HOT
SWITCH
BATTERY
BATT/EXT
POWER
SWITCH
OFF
ESSN
BATTERY
WARM
RELAY
BATTERY
RELAY
EXT
BATT
BATT WARM
SWITCH
ESSN
BUS
ESSN
BUS
RELAY
F90-068
Figure 7−22. Battery Power and External Power Subsystem Block Diagram
Aircraft Lighting:
Aircraft Interior Lighting:
Cockpit:
Floodlight
(1)
Map Light
(1)
Instrument Floodlights
(3) (Powered By Essential Bus)
Main Cabin:
Threshold Lights
7−34
(2)
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
Baggage Compartment:
Floodlight
(1)
Aircraft Exterior Lighting:
Nose:
Fixed Landing Light
(1)
Fixed Hover Light
(1)
Empennage:
Left End of Horizontal Stabilizer:
Red Navigation Light
(1)
Right End of Horizontal Stabilizer:
Green Navigation Light (1)
Top Center of Stabilizer:
Flashing Red Anticollision Light (1)
White Navigation Light (1)
Bottom of Tailboom, Forward of Thruster:
Flashing Red Anticollision Light (1)
White Navigation Light (1)
7−13. ENVIRONMENTAL CONTROL
The environmental control system for the helicopter consists of the ventilation sys­
tem and the heat/defog system.
Ventilation System:
Ambient air is taken in through an inlet in the right side of the upper cowling,
is directed through a water separator and a two-speed fan, and into a manifold
that distributes the air to the cockpit and to the cabin - then out of a port in the
baggage compartment door. In the cockpit, four adjustable gaspers, two on the wind­
shield's center bow blow outboard toward the pilots' heads, and two on the forward
door frame blow inboard toward their lower torsos. Six adjustable gaspers are
mounted in the ceiling of the cabin. The fan speed switch is located on the Utility
Panel.
Secondary ventilation for the cockpit is provided by two conventional clear plastic
adjustable snap vents in the window of each cockpit door.
Heat/Defog System:
The heat source is bleed air from the compressors of the two engines. This hot air
is directed through a pilot-operated on/off valve located on the Utility panel to a
Reissue 3
Original
7−35
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
pair of ejectors that mix bleed air and ambient air to a desired temperature and
flow rate. One ejector serves the cockpit; the other serves the cabin.
The cabin ejector is located low on the right side of the cabin just aft of the door.
Its discharge air is directed across the cabin under the rear seats. An adjusting
lever for controlling the bleed air admitted to the ejector, and so the discharge volume,
is recessed in the wall at head height directly above the ejector.
CHECK
VALVES
ENGINE
ENGINE
PASSENGER COMPARTMENT
START−UP
LOCK OUT
FLOW
CONTROL
VALVES
PASSENGER
COMPARTMENT
EJECTORS
HEAT ON/OFF
SWITCH
FLOW CONTROL
SHUT−OFF VALVE
(ON/OFF)
FLOW CONTROL
VALVES
DEFOGGING
MANIFOLDS
PILOT HEAT
EJECTORS
FOOT HEATERS
FOOT HEATERS
CONTROL VALVES
CREW STATION
F90−042
Figure 7−23. Heat/Defog System Schematic
The cockpit ejector is located in the compartment below the pilot's seat, and is oper­
ated by a push/pull control mounted vertically along the right hand side of the
console. From the ejector, warm air is ducted forward to two aft-facing nozzles above
and forward of the pilots' feet, and to a pair of nozzles along the bottom of the
upper windshield panels to defog them. Each pilot has a push/pull knob located
under the instrument panel to operate a butterfly valve that modulates the airflow
toward his/her feet.
An automatic disconnect monitored by the IIDS cuts off all bleed air whenever either
engine becomes inoperative in flight to maximize the operating engine's power output
to the rotor. This cutoff function maybe overridden by placing the CAB HEAT switch
in the OVRD position.
7−36
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
7−14. INTEGRATED INSTRUMENTATION DISPLAY SYSTEM (IIDS)
General
The IIDS provides for the monitoring and display of various aircraft
parameters and for caution/warning annunciation. The baseline config­
uration includes a set of engine, drive train, rotor, NOTAR, electrical,
fuel, hydraulic, and caution/warning indicators. It also incorporates a
built-in rotor and NOTAR fan balance system and stores system oper­
ating and exceedance parameters for enhanced maintainability.
The IIDS accepts analog and discrete inputs from various aircraft sub­
system transducers and provides signal conditioning and conversion
to digital format. Once converted to digital format, this information
is provided to the display electronics for the cockpit display and to a
serial port for access by a data recorder or computer. Also, limit checking
on certain parameters is performed to provide the caution/warning an­
nunciation. The display is a color, Liquid Crystal Display (LCD) panel
which allows the flexibility of integrating the specified sensor data and
caution/warning information onto a display packaged as one unit.
Built−In−Test
Three levels of Built-in-Test (BIT) are used to determine system health,
including Power-up, Continuous, and Commanded BIT. Power-up diag­
nostics will check the health of each function or module within the IIDS
and display this test status. Continuous testing checks the operation
of the IIDS during aircraft operation and displays and/or logs any fail­
ures. Commanded BIT, initiated using the IIDS keyboard, performs
a display test, along with those tests performed during Continuous BIT.
The display is put into ``lamp test'' mode, where all segments are acti­
vated, so that the display can be visually inspected for segment failures.
Both Power-up and Commanded BIT test the two engine and the trans­
mission fire detectors, and the bleed air leak detector (if installed).
Reissue 3
Original
7−37
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FUEL
SYSTEM
POWERPLANT
SYSTEM
DRIVE
SYSTEM
ROTOR
SYSTEM
BALANCE
MONITORING
SYSTEM
NOTAR
SYSTEM
HYDRAULIC
SYSTEM
ELECTRICAL
SYSTEM
INTEGRATED INSTRUMENT
DISPLAY SYSTEM (IIDS)
AIRFRAME
SYSTEM
F90−048A
Figure 7−24. IIDS System Monitoring
BIT
Failures
BIT failures are stored in non-volatile memory to assist in three situa­
tions:
First, a transient or intermittent failure;
Second, a situation where the pilot observed a problem with the IIDS
but didn't notice any failure annunciation;
Third, ease of IIDS maintenance on and off the aircraft. These fault
words are stored in the Fault Log when a BIT failure was detected
in the IIDS, BMS, EEC, or aircraft transducers/sensors, and can be
examined through the IIDS display or ground based maintenance com­
puter (GBMC).
When the testing determines that an internal fault exists, the appropri­
ate redundant function, if such redundant system exists, will be com­
manded to assume the primary role. The redundant functions shall
be sufficiently isolated such that a failure of the function will not cause
7−38
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ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
the failure of another function. These fault monitoring provisions are
implemented using hardware Built-in-Test Equipment (BITE) and soft­
ware diagnostics, allowing isolation of failures to at least the internal
module level. In addition, provisions are made to check operation of
the transducers and sensors and provide an appropriate maintenance
alert.
Any sensor that can be checked for proper function and is determined
to have failed causes an IIDS caution annunciation and a blanking of
the digit display for that parameter. No Fault Log is created.
The following are exceptions to the above:
1. A failure of a sensor for the primary display parameters (EGT,
Torque, NR, and NP) causes both the vertical scale and digit value
to blank.
2. If the voltage for the fuel probes (Battery Bus voltage input) drops
below the specified operating low limit of 18 volts for more than
40 seconds, the low voltage indication shall be to blank the segments
in the fuel quantity vertical scale. The digit quantity shall remain
active. When the probe voltage goes back above 18 volts for more
than one second, the vertical scales shall be illuminated. A failure
of one of the fuel probes causes only the digit values to blank whereas
the failure of both probes causes both the vertical scale and digit
value to blank.
3. If the parameters displayed on the alphanumeric display (Pressure/
Density Altitude, CLP, and Hydraulic Pressure) are out-of-range,
the display will read NOT VALD.
The functional architecture of the IIDS to meet these design goals and
the operational requirements of the aircraft is shown in Figure 7-24.
System
Software
Architecture
SYSTEM OPERATING PROGRAM: The System Operating Program
provides the programming and functions controlling the data collection,
displays and formatting, key entry functions, date/time clock, cautions
and warnings, exceedance detection, memories and BIT feature.
Primary and
Secondary
Displays
The integrated display is divided into two separate displays. The prima­
ry is on the right side and the secondary is on the left.
The primary display includes the following information.
Power turbine speed - NP
Rotor speed - NR
Measured gas temperature - EGT
Engine Torque - TORQUE
NR and NP are displayed with three vertical bargraphs and a digit
value of NR displayed in the center.
Reissue 3
Original
7−39
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
NR and NP speed increase: Since the required NP/NR setting under
different flight conditions changes, the IIDS advises the pilot to make
the respective NP/NR changes when airspeed is 47 KIAS and below.
Torque display: Displayed in % torque. The IIDS obtains engine torque
from the EEC. If the EEC fails, the IIDS calculates torque by using
NG, OAT, and pressure altitude measurements. The vertical bargraphs
and three digit indicators on this display indicate torque in percent
(%). The vertical bar has four ranges as defined below:
Green segments indicate continuous operating range including Maxi­
mum Continuous Power (MCP).
Yellow segments indicate:
Transient Take Off Power (TOP) operating range (10 second limit)
OEI operating range (2.5 minutes)
Top red segments - do not exceed limit.
NOTE: Even though the IIDS displays engine torque, the transmission sets the torque
limit for helicopter operations, and therefore, the displayed torque limits are
lower than those for the engine as stated in the Pratt & Whitney Maintenance
Manual.
EGT is indicated by two vertical bargraphs and a three digit indicator
showing EGT in 1°C increments. Displayed on the IIDS as EGT. Pratt
& Whitney refers to this measurement as MGT (Measured Gas Tempera­
ture). The vertical bargraph has four ranges as defined by the display
mode; they are:
Green segments - continuous operating range (MCP operating range)
Yellow segments - transient operating range (TOP or OEI)
Top red segment - do not exceed limit
NOTE: The IIDS provides a time count−down on the alphanumeric display when the
pilot enters TOP, OEI, or transient flight conditions. Should the pilot exceed
the count−down, the IIDS then provides an time overcount, and exceedance
and data logs are created.
Warning annunciators in red are for EGT, Torque, NR, NP, and EEC FAIL.
Caution annunciators in yellow are for EEC minor fault, EEC MAN
(manual) mode, and OEI (one engine inoperative).
In the secondary display, caution annunciators in yellow are given
for engine chips, engine oil temperature, high or low, engine oil pressure
high or low, generator load high, generator out, NG high, transmission
chips, transmission oil temperature high or low, fuel pressure low, fuel
filter impending by-pass, crossfeed valve open, fuel valve closed, battery
warm, rotor brake, hydraulic system status, baggage door open and
IIDS status.
Engine oil pressure display: Displayed in % psi, and is a function of
NG speed and engine oil temperature.
7−40
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
Engine oil temperature display - °C
Gas producer turbine speed display - %NG
Transmission oil pressure display: Displayed in % PSI, and is a function
of NR speed and transmission oil pressure.
Transmission oil temperature display - °C
Generator load display - %LOAD
Warning Annunciators displayed in red are shown for engine fire, engine
oil temperature high, engine oil pressure high or low, NG high or low,
transmission area fire, transmission oil pressure high or low, fuel quanti­
ty low CAB HEAT (bleed air leak), and BAT HOT.
Display
Brightness
Controls
Day or night modes may be selected using the Light Master switch
located on the Lighting Control Panel. Placing the Light Master switch
ON selects night mode.
The display brightness is adjustable using the inner ring of the IIDS
control potentiometer also located on the Lighting Control Panel.
When in the night mode, the IIDS will automatically increase display
brightness when a caution/warning message is received and displayed.
To return to the preset brightness, press the CLR key momentarily.
LIGHTING CONTROL
LIGHT MASTER
SWITCH
LT MSTR
ON
OFF
IIDS
CONSOLE
OFF
FLOOD
STROBE
POSN
ON
ON
OFF
OFF
OFF
BOTH
CKP
IIDS DISPLAY
BRIGHTNESS
CONTROL
INSTR
AREA
CAB
OFF
F90−049A
Figure 7−25. IIDS Display Brightness Control
Alphanumeric
Display
The IIDS has a 2 line by 16 character alphanumeric display. This display
allows messages to be displayed regarding systems limit exceedance,
condition, various cautions and warnings as well as expanded features
of the IIDS to be viewed by the pilot. Yellow and red segments are located
Reissue 3
Original
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CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
to the left of each line that indicate if the associated message is a caution
or a warning. The expanded features of the IIDS are selected in conjunc­
tion with the IIDS keyboard.
Certain conditions will cause the alphanumeric display to automatically
display a message.
At start-up, and if required during flight, messages are displayed on
the alphanumeric display automatically. A list of these messages is
found in Table 7-1. This table also defines the priority of the message
to be displayed, the classification of the message (warning/caution/advi­
sory W/C/A), and whether the message can be cleared (by pressing the
CLR button) from the display.
NOTE: IIDS menu functions may be lost if the MENU key is pressed immediately after
a W/C/A message is cleared. Pilots should wait two or more seconds before
selecting a menu option.
AOG
Logic
The IIDS uses the following logic to determine an aircraft on-ground/offground condition. The IIDS uses this information to enable or disable
certain caution/warning, indications and alphanumeric display advisory
messages.
Aircraft on-ground if:
1. NR 80%
OR
Aircraft on-ground if:
1. NR >80%, and
2. CLP <5%, and
3. Torque (either engine) >10%
Otherwise, the aircraft is off-ground. The transition from one condition
to the other is not recognized until after the new condition has existed
for 5 seconds.
7−42
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Systems Description
NOTE: Advisory messages may not indicate a malfunction or emergency.
WARNING
ANNUNCIATOR (RED)
. . . . . . . . . . . . . . .
CAUTION ANNUNCIATOR
(YELLOW)
. . . . . . . . . . . . . . .
WARNING
ANNUNCIATOR (RED)
CAUTION ANNUNCIATOR
(YELLOW)
TORQUE
NR
NP
NP
ALPHANUMERIC
MESSAGE
DISPLAY
EGT
ENG
OUT
F90−025
Figure 7−26. Alphanumeric Display
Table 7−1. Automatic Alphanumeric Display Warning/Caution/Advisory Messages
SAMPLE MESSAGE
(Fault)
ENG POWER CHECK
L PA CK NG -1.8
LPA CK EGT-11.2
OVR TORQ LFT 0:10
OVR TORQ RT 0:10
OVR EGT LFT 0:10
OVR EGT RT 0:10
OVR NG LFT 0:10
OVR NG RT 0:10
CAUSE FOR
DISPLAY
W/C/A CLR
CORRECTIVE ACTION
Invalid performance
margin (power check
failed)
W
YES
Advise Maintenance
MTO or OEI
overcount
W
NO
Advise Maintenance
PRES 1 =
0 PSI
PRES 2 = 1000 PSI
Hydraulic system
status: activated on
hydraulic caution
indication
C
YES
Perform malfunction
procedure. Ref. Section
III
TEMPERATURE
Hydraulic system
overtemperature
C
YES
L ENG OIL COLD
Engine oil
temperature cold
(Starting)
C
NO
RIGHT STAB FAIL
Right Stabilizer
Actuator Failure
C
YES
LEFT STAB FAIL
Left Stabilizer
Actuator Failure
C
YES
TOTAL STAB FAIL
Both Stabilizer
Actuator Failure
C
YES
Reissue 3
Original
Perform malfunction
procedure. Ref. Section
III
Start engine with engine
control in IDLE. Do not
advance to FLY until
message blanks
Perform malfunction
procedure. Ref. Section
III
7−43
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 7−1. Automatic Alphanumeric Display Warning/Caution/Advisory Messages
SAMPLE MESSAGE
(Fault)
CHK BMS SENSOR
TORQ LFT 2:30
TORQ RT 2:30
EGT LFT 2:30
EGT RT 2:30
NG LFT 2 :30
NG RT 2:30
CARGO HOOK OPEN
IPS BYPASS
BATT DISCHARGE
EXTNGSHR PRESS LO
RECORDING DATA
DATA XFER CMPL
CHECK FAULT LOG
CHK EXCEED LOG
CHECK ROTOR BAL
CHECK NOTAR BAL
PRATT & WHITNEY
CAUSE FOR
DISPLAY
W/C/A CLR
CORRECTIVE ACTION
BMS sensor(s)
failure2
C
YES
Advise maintenance
TOP or OEI
countdown
A
NO
N/A
A
YES
N/A
A
YES
Ref. Section III
A
YES
N/A
A
YES
Advise Maintenance
A
NO
N/A
A
YES
N/A
A
YES
Advise Maintenance
A
YES
Advise Maintenance
A
YES
Advise Maintenance
A
YES
Advise Maintenance
A
YES
N/A
Cargo hook open
Particle separator
clogged: IPS in
bypass
Battery Discharging
Optional fire
extinguishing system
bottle pressure low
Crew commanded
data record
Download of data logs
to ground based
computers
Fault Log during
flight2,3
Exceedance Log
during flight3
Main rotor out of
balance
NOTAR fan out of
balance
Engine
Configuration4
NOTE: 1.With a single system failure, this message is displayed when the failed system
pressure decreases to 250 PSI. This message will reappear when remaining
operating system pressure decreases to 500 PSI.
2.This caution does not affect dispatchability.
3.These messages are generated for conditions that create a fault log or an
exceedance log and are displayed only when the aircraft is on−ground as
determined by the AOG logic.
4.This message displayed for 5 seconds following the power−up ‘‘Lamp Test’’.
7−44
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Systems Description
7−15. IIDS DATA STORAGE
Data Storage
Selected information that is monitored by the IIDS for display is also
stored by the IIDS. Information is stored in non-volatile memory and
is available by selecting various menu functions through the front panel
keys. All information is available using a ground based maintenance
computer (GBMC). Only the Data Log and Cumulative Log are not
viewable on the alphanumeric display. The operating data is stored
in one of six data records.
The data records are:
LOG TYPE
A/N DISPLAY
Data Log
NO
Cumulative Log
NO
Exceedance Log
YES
Fault Log
YES
Trend Log
YES
Setup Log
YES
Data Logs
The data log provides one and a half minutes of data collection. The
data is recorded in a continuous memory buffer ``loop'' and will be contin­
uously over-written unless an exceedance occurs, or the crew requests
a record of an event. Exceedances generate both data logs and excee­
dance logs. The data log record provides a ``window in time'' to examine
events around an exceedance or other incident. The data log can store
five of these events. This information is accessed by the GBMC only.
Pilots may generate a data log by first clearing the alphanumeric display,
then pressing and holding the “REC” button for 7 to 10 seconds before
releasing. The message RECORDING DATA will then be displayed on
the alphanumeric display.
Cumulative Log
The cumulative log retains data concerning the aircraft operational his­
tory and current configuration. As the aircraft configuration changes
(e.g. component changes) the Cumulative Log will be updated by the
maintainer on the GBMC. The IIDS will only retain one Cumulative
Log in memory.
NOTE: Time Summary Menu procedure (Ref. Figure 7−29) may be used to access
cumulative usage data as well as flight time data.
Exceedance
Log
The exceedance Log provides a ``snapshot'' record of the parameter data
at a particular moment in time. This type of record occurs whenever
a parameter exceedance is detected. This recording function is only
Reissue 3
Original
7−45
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
active when NG for either engine AND NR is greater than 50 % AND
EGT on either engine is greater than 400°C
Fault
Log
IIDS Setup Log
IIDS
Keyboard
This feature is capable of storing 100 exceedance Logs. Exceedances
are recorded for EGT, engine torque, transmission torque, NG, NP, NR
(high), engine oil pressure (low), transmission oil pressure (low), and
cargo hook.
Exceedance logs maybe either recorded or downloaded to the GBMC.
Perform Exceedance Log Menu procedure (Figure 7-42) to access cumu­
lative usage data.
The Fault Log contains data associated with fault discrete data from
the EEC's and a BIT failure that was detected in the IIDS, BMS, or
aircraft transducers/sensors. This type of log is recorded whenever an
IIDS, EEC, or aircraft sensor fault is detected. The system is capable
of storing 100 Fault Logs.
Fault logs maybe either recorded or downloaded to the GBMC.
Perform the Fault Log Menu procedure to access data (Figure 7-44).
(Ref. Figure 7-45) IIDS setup contains data that reflects the current
configuration of the aircraft, such as, aircraft serial number, engine
type installed, engine serial number, fuel calibration, operating soft­
ware, etc.
On power up, the IIDS uses information in the setup log to compare
the current Torque and EGT trim values from the EEC to the values
stored in the IIDS setup log to assure the data collected by the IIDS
remains with the respective engine. If there is a discrepancy, a fault
log is created and certain engine ASCM functions are disabled for the
affected engine(s): Exceedance Logs for NG, NP, Torque, EGT; Power
Assurance function (including trend logs); and Cumulative Logs (cycle
counting, SSO, FSO, TSN, and engine run time).
To recover from this disable function, the Setup Log must be revised
to match the values from that specific engine(s) through the GBMC.
Once the Setup Log has been revised, a power-up of the IIDS will verify
the new data. If the new values match, all engine ASCM functions are
restored.
The IIDS features 7 keys on the right side of the front face to allow
the pilot access to the various functions/programs by paging through
the menus. The keys include:
``CLR'' (clear): Used to blank the alphanumeric display and exit all
menu functions if pressed for more than 1.5 seconds. If pressed for less
than 1.5 seconds in the Night Mode after a C/W/A event, the CLR key
resets the intensity to the previous setting.
7−46
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
MENU: Used to access the next higher level of the menu structure
or to enter the top level menu from display blanked and to return to
the ``action'' menu with edit fields not updated.
UP ARROW : Used to scroll between menu and submenu names,
or between data and message items. Holding this key for more than
2 seconds initiates automatic scrolling, at approximately one item per
second. When the scrolling reaches the end of the menu the scrolling
feature loops back to the start of the menu.
DN (down) ARROW: Same as the UP ARROW, except scrolls in
the opposite direction.
ENT (enter): Used to enter a menu or submenu after it has been selected
with the ``'' or ``'' keys, enter an ``Action'' field within a menu selection
that is bracketed by ``< >'' to allow editing, and to advance to the next
edit digit (or field within the ``Action'' field. The digit (or field) that can
be edited will flash.
CLR
MENU
``REC'' (record): Used to initiate crew requested Data Log and to enter
into memory data that is used to initialize the TIME/DATE, ENGINE
PARM, and Cargo Hook CALIB CODE and FUEL CALIBRATION func­
tions in the IIDS. When the key is pressed for more that 7 seconds,
the parameter data from 45 seconds prior to and 45 seconds after key
activation, is stored in nonvolatile memory. The message RECORDING
DATA is displayed on the alphanumeric display during this time.
ENT
REC
DISP
J1
F90−050
``DISP'': Used to change the display from ``display by exception'' to ``con­
tinuous display'' when the key is pressed for less than 1.5 seconds. In
the exception mode, the secondary display screen area is blank unless
one of the limits is within a predetermined range of it's caution limit
value. When this happens, the digit display of the particular limit will
revert to continuous display until the parameter value drops below the
predetermined threshold. If the exceedance parameter enters caution
or warning range the appropriate caution or warning displays are illumi­
nated.
When the ``DISP'' key is held for more than 1.5 seconds the IIDS performs
a BIT test and the front panel display will show all LCD segments in
a lamp test mode.
Reissue 3
Revision 2
7−47
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
7−16. BALANCE MONITORING SYSTEM
NOTE: Helicopter gross weight should be at 5200 300 LBS before performing ‘‘Main
Rotor Balance’’ procedure.
Standard BMS
Program
The BMS program is an integrated vibration monitoring system which
calculates and displays balance solutions for both main rotor and NO­
TAR fan. The intention of this integrated balance system is to eliminate
the requirement to fly dedicated tracking/balance flights.
The system is linked to three vibration sensors on the airframe and
two position pickups on the main rotor and the NOTAR fan. The stan­
dard BMS program is a ``smart chart'' system. For most balancing actions
the user will simply follow the directions of the BMS Alpha-numeric
display (Ref. Figure 7-30 thru Figure 7-41). The normal sequence of
events is for the pilot to request the BMS program from the IIDS by
pressing the ``MENU'' key on the IIDS panel and paging down the menu
to BMS. The BMS system will then analyze the input from the rotor/fan
sensors and calculate a correction and display this information in the
IIDS Alpha-numeric display.
ÎÎ
ÎÎ
1.
2.
3.
4.
5.
IIDS
BMS SIGNAL PROCESSING UNIT
BMS SENSOR CABLE HARNESS
AZIMUTH SENSOR (MAG PICKUP/PHOTOCELL)
VIBRATION SENSOR (VELOCIMETER)
F90−078
Figure 7−27. Balance Monitoring System Installation
Optional
Spectrum
Analyzer
7−48
An optional item to the BMS is a Spectrum Analyzer Vibralog. The
software for this program resides within the GBMC. Spectrum analysis
allows downloading to the GBMC and viewing of the entire vibration
spectrum of the rotor and the NOTAR fan. The system allows the
operator to analyze vibrations, other than rotor/fan, and determine the
probable source by comparison with known component frequencies.
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Systems Description
7−17. IIDS MENU STRUCTURES
TOP LEVEL
ELAPSED TIME MM.SS
TIME SUMMARY
POWER CHECK
BALANCE MONITOR
AIRCRAFT MONITOR
``ENT'' Key resets, starts and stops timer (alternate action);
``CLR'' Key exits function and resets timer
ENT
For expanded menu structure
Ref. Figure 7-29
ENT
For expanded menu structure
Ref. Section V Figure 5-21
ENT
For expanded menu structure
Ref. Figure 7-30 thru Figure 7-41
ENT
For expanded menu structure
Ref. Figure 7-42 thru Figure 7-45
CLPXXX PERCENT
Continuous display of collective position
PRES ALT XXXXFT
DENS ALT XXXXFT
Continuous display of altitude
FUEL CALIBRATION
SET ENGINE PARM
TIME/DATE
HOOK WT XXXX LBS
ENT
For expanded menu structure
Ref. Figure 7-46
ENT
For expanded menu structure
Ref. Figure 7-47
ENT
For expanded menu structure
Ref. Figure 7-48
ENT
For expanded menu structure
Ref. Section X
F90−071A
Figure 7−28. IIDS Top Level Menus
Reissue 3
Original
7−49
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
TOP LEVEL
THIRD LEVEL
ENT
TIME SUMMARY
LST FLT TIME
TOT FLT HR
TOT FLIGHTS
ENT
LFT ENGINE TIME
NOTE 1
RT ENGINE TIME
GEAR BOX
TSO =
POWER MODULE
TSO=
IMPELLER CYCLE
CNT LST FLT=
IMPELLER CYCLE
CNT ACCUM =
CMPSR TURB CYCLE
CNT LST FLT=
CMPSR TURB CYCLE
CNT ACCUM=
POWER TURB CYCLE
CNT LST FLT=
POWER TURB CYCLE
CNT ACCUM=
NOTE 1: THIRD LEVEL MENU FOR RIGHT ENGINE
SAME AS FOR LEFT ENGINE
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−072
Figure 7−29. Time Summary
7−50
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
BALANCE MONITOR
SECOND LEVEL
MAIN ROTOR
BALANCE
Systems Description
THIRD LEVEL
FOURTH LEVEL
COLLECT M/R DATA
RUN XX RPM XXX
FLY 104% GROUND
PRESS REC
RUN XX M/R
MEASUREMENTS
ACQUIRING
104% GND LAT
NOTE 2
MAIN ROTOR TRACK
NOTE 3
NOTAR
BALANCE
MAIN ROTOR
CONFIGURATION
SPECTRUM
MAIN ROTOR
SOLUTION OPTIONS
104% GND LAT
X.XX IPS AT YY.YY
NOTE 1
BMS ADVISORY LOG
DISPLAY M/R
SOLUTION RUN XX
ACQUISITION
COMPLETE
FLY HOVER IGE
PRESS REC
NOTE 2
BMS FAULT LOG
ACQUIRING
HOVER IGE LAT
NOTE 3
BMS VERSION LOG
HOVER IGE LAT
X.XX IPS AT YY.YY
NOTE 1
BMS MAINTENANCE
ACQUISITION
COMPLETE
FLY 120 KIAS
PRESS REC
FLY 80 KIAS
PRESS REC
ACQUIRING
120 KIAS LAT
NOTE 2
NOTE 2
ACQUIRING
80 KIAS LAT
NOTE 3
120 KIAS LAT
X.XX IPS AT YY.YY
NOTE 3
NOTE 1: WHEN COMPLETED, MESSAGE IS DISPLAYED
FOR 1 SECOND
80 KIAS LAT
X.XX IPS AT YY.YY
NOTE 2: AUTOMATICALLY STEPS THROUGH ACQUIRING
MEASUREMENTS SPECIFIED FOR THIS REGIME.
NOTE 2
ACQUIRING
120 KIAS VERT
NOTE 2
NOTE 3: WHEN COMPLETE, THE RESULT IS DISPLAYED
FOR 4 SECONDS AND THE DISPLAY GOES TO
NEXT REGIME.
NOTE 4: WHEN COMPLETE, THE RESULT IS DISPLAYED
FOR 4 SECONDS
NOTE 4
120 KIAS VERT
X.XX IPS AT YY.YY
ACQUIRING
80 KIAS VERT
NOTE 3
80 KIAS VERT
X.XX IPS AT YY.YY
NOTE 1
ACQUISITION
COMPLETE
NOTE 1
NOTE 5: THE DISPLAY GOES BACK TO THE FIRST
REGIME WHEN THE ABOVE DATA HAS BEEN
COLLECTED
ACQUISITION
COMPLETE
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
NOTE 5
REDO 104% GND
PRESS REC
MENU
F90−136
Figure 7−30. Balance Monitor, Main Rotor Balance
Reissue 3
Original
7−51
CSP−900RFM206A−1
Systems Description
TOP LEVEL
BALANCE MONITOR
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
THIRD LEVEL
MAIN ROTOR
BALANCE
MAIN ROTOR TRACK
NOTAR
BALANCE
FOURTH LEVEL
COLLECT M/R
DATA RUN XX
104% GND LAT
X.XX IPS AT YY.YY
RUN XX M/R
MEASUREMENTS
HOVER IGE LAT
X.XX IPS AT YY.YY
MAIN ROTOR
CONFIGURATION
SPECTRUM
MAIN ROTOR
SOLUTION OPTIONS
BMS ADVISORY LOG
DISPLAY M/R
SOLUTION RUN XX
80 KIAS LAT
X.XX IPS AT YY.YY
80 KIAS VERT
X.XX IPS AT YY.YY
120 KIAS LAT
X.XX IPS AT YY.YY
120 KIAS VERT
X.XX IPS AT YY.YY
BMS FAULT LOG
OR
note 1
NOT ACQUIRED
BMS VERSION LOG
BMS MAINTENANCE
NOTE 1: COULD APPLY FOR EACH REGIME
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−137
Figure 7−31. Balance Monitor, Run M/R Measurements
7−52
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
SECOND LEVEL
BALANCE MONITOR
MAIN ROTOR
BALANCE
THIRD LEVEL
COLLECT M/R
DATA RUN XX
MAIN ROTOR TRACK
RUN XX M/R
MEASUREMENTS
NOTAR
BALANCE
MAIN ROTOR
CONFIGURATION
MAIN ROTOR
SOLUTION OPTIONS
SPECTRUM
BMS ADVISORY LOG
DISPLAY M/R
SOLUTION RUN XX
CSP−900RFM206A−1
Systems Description
FOURTH LEVEL
NOTE 1
BLADE 1 HUB WT
<XXX> GRAMS
THROUGH
BLADE 5 HUB WT
<XXX> GRAMS
NOTE 1
BLADE 1 TRIM TAB
<XXX> MILS
THROUGH
NOTE 1 AND 2
BLADE 5 TRIM TAB
<XXX> MILS
NOTE 1
BLADE 1 PC WT
<XXX> GRAMS
THROUGH
BMS FAULT LOG
NOTE 1 AND 2
NOTE 1 AND 2
BLADE 5 PC WT
<XXX> GRAMS
BMS VERSION LOG
BMS MAINTENANCE
NOTE 1: “ENT” KEY SELECTS DIGITS TO BE EDITED,
AND KEYS INCREASE/DECREASE DIGIT VALUE,
“REC” KEY STORES SELECTED VALUES, “CLR” EXITS
OUT OF MENU TO DISPLAY BLANK.
NOTE 2: STEP THROUGH BLADES SEQUENTIALLY
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−139
Figure 7−32. Balance Monitor, Main Rotor Configuration
Reissue 3
Original
7−53
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
SECOND LEVEL
THIRD LEVEL
MAIN ROTOR
BALANCE
COLLECT M/R
DATA RUN XX
FOURTH LEVEL
NOTE 1
BALANCE MONITOR
ADJUSTMENTS USED
<PCL/TAB/WEIGHT>
OR
MAIN ROTOR TRACK
RUN XX M/R
MEASUREMENTS
NOTE 2
<PCL/TAB>
OR
NOTAR
BALANCE
MAIN ROTOR
CONFIGURATION
NOTE 2
<PCL WEIGHT>
OR
SPECTRUM
MAIN ROTOR
SOLUTION OPTIONS
<TAB/WEIGHT>
DISPLAY M/R
SOLUTION RUN XX
COMPUTE
<ENTIRE SOLTN>
NOTE 1
BMS ADVISORY LOG
OR
NOTE 2
COMPUTE
<GND SOLTN ONLY>
BMS FAULT LOG
OR
NOTE 2
COMPUTE
<80 KIAS SOLUTION>
BMS VERSION LOG
BMS MAINTENANCE
NOTE 1: “ENT” KEY SELECTS FIELD TO BE EDITED,
AND KEYS CHANGE FIELD SELECTION,
“REC” KEY STORES THE SELECTION, “CLR” EXITS
OUT OF MENU TO DISPLAY BLANK.
NOTE 2: OPERATOR OPTIONAL SELECTION
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−142
Figure 7−33. Balance Monitor, Main Rotor Solution Options
7−54
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
BALANCE MONITOR
SECOND LEVEL
THIRD LEVEL
MAIN ROTOR
BALANCE
MAIN ROTOR TRACK
NOTAR
BALANCE
CSP−900RFM206A−1
Systems Description
FOURTH LEVEL
COLLECT M/R
DATA RUN XX
COMPUTING M/R
SOLTN RUN XX.XX
RUN XX M/R
MEASUREMENTS
PREDICTED VIBS
BELOW X.XX IPS
MAIN ROTOR
CONFIGURATION
NOTE 1
AUTOMATIC
PCSE ADD XXX.X G
BLD X PCSE <NOT MADE>
NOTE 2
OR
SPECTRUM
MAIN ROTOR
SOLUTION OPTIONS
DISPLAY M/R
SOLUTION RUN XX
BMS ADVISORY LOG
PCSE SUB XXX.X G
BLD X PCSE <NOT MADE>
HUB ADD XXX.X G
BLD X <NOT MADE>
NOTE 2
NOTE 2
OR
BMS FAULT LOG
HUB SUB XXX.X G
BLD X <NOT MADE>
NOTE 2
BMS VERSION LOG
TAB DWN XXX MILS
BLD X <NOT MADE>
NOTE 2
OR
BMS MAINTENANCE
TAB UP XXX MILS
BLD X <NOT MADE>
NOTE 2
PCL UP XX.X FLAT
BLD X <NOT MADE>
NOTE 2
OR
NOTE 1: MESSAGE FLASHING IF COMPUTING A SOLUTION
PCL DN XX.X FLAT
BLD X <NOT MADE>
NOTE 2
ENTIRE SOLTN
<NOT MADE>
NOTE 3
OR
NOTE 2: “ENT” KEY SELECTS FIELD TO BE EDITED, AND KEYS
CHANGE FIELD SELECTION FROM NOT MADE TO MADE, “REC” KEY STORES
SELECTION, “CLR” EXITS TO BLANK DISPLAY.
NOTE 3: SELECTIONS ARE NOT MADE, ALL MADE, OR AS SELECTED
NOTE 4: SELECTIONS ARE ALL MADE, OR AS SELECTED
GND SOLTN ONLY
<NOT MADE>
OR
80 KIAS SOLTN
<NOT MADE>
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
NOTE 4
NOTE 4
MENU
F90−143
Figure 7−34. Balance Monitor, Display M/R Solution
Reissue 3
Original
7−55
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
SECOND LEVEL
BALANCE MONITOR
MAIN ROTOR
BALANCE
THIRD LEVEL
DEFAULT
MAIN ROTOR TRACK
FLASH STROBE
BLD SPREAD <ON>
OR
NOTAR
BALANCE
FLASH STROBE
BLD SPREAD <OFF>
SPECTRUM
BMS ADVISORY LOG
BMS FAULT LOG
BMS VERSION LOG
BMS MAINTENANCE
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−144
Figure 7−35. Balance Monitor, M/R Track
7−56
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
BALANCE MONITOR
SECOND LEVEL
MAIN ROTOR
BALANCE
CSP−900RFM206A−1
Systems Description
THIRD LEVEL
FOURTH LEVEL
COLLECT NOTAR
RUN XX RPM XXXX
FLY 104% GND
PRESS REC
NOTE 1
RUN XX NOTAR
MEASUREMENTS
MAIN ROTOR TRACK
ACQUIRING
104% GND RADIAL
NOTE 2
NOTAR WEIGHT
CONFIGURATION
NOTAR
BALANCE
104% GND RADIAL
X.XX IPS AT YY.YY
NOTE 3
DISPLAY NOTAR
SOLUTION RUN XX
SPECTRUM
ACQUISITION
COMPLETE
BMS ADVISORY LOG
BMS FAULT LOG
BMS VERSION LOG
BMS MAINTENANCE
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
NOTE 1:AUTOMATICALLY STEPS THROUGH ACQUIRING
MEASUREMENTS SPECIFIED FOR THIS REGIME.
NOTE 2: WHEN COMPLETE, RESULT DISPLAYED FOR 4 SECONDS.
NOTE 3: WHEN COMPLETE, MESSAGE DISPLAYED FOR 1 SECOND
F90−145
Figure 7−36. Balance Monitor, NOTAR Balance
Reissue 3
Original
7−57
CSP−900RFM206A−1
Systems Description
TOP LEVEL
BALANCE MONITOR
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
THIRD LEVEL
FOURTH LEVEL
MAIN ROTOR
BALANCE
MAIN ROTOR
TRACK
NOTAR
BALANCE
COLLECT
NOTAR DATA
104% GND RADIAL
X.XX IPS AT YY:YY
OR
NOTAR
MEASUREMENTS
SPECTRUM
NOT ACQUIRED
NOTE 1
BMS ADVISORY LOG
STD 1 WEIGHT
<XX.X> GRAMS
NOTE 1
NOTAR WEIGHT
CONFIGURATION
BMS FAULT LOG
STD 13 WEIGHT
<XX.X> GRAMS
NOTE 2
COMPUTING NOTAR
SOLTN RUN XX.XX
BMS VERSION LOG
AUTOMATIC
DISPLAY NOTAR
SOLUTION
BMS MAINTENANCE
PREDICTED VIBS
BELOW X.XX IPS
NOTE 3
ADD XXX GRAMS
STD XX <NOT MADE>
NOTE 1: “ENT” KEY SELECTS DIGITS TO BE EDITED,
AND KEYS INCREASE/DECREASE DIGIT VALUE,
NOTE 3
OR
“REC” KEY STORES SELECTED VALUES, “CLR” EXITS
OUT OF MENU TO DISPLAY BLANK.
SUB XXX GRAMS
STD XX <NOT MADE>
NOTE 2: MESSAGE FLASHING IF COMPUTING A SOLUTION
NOTE 4
NOTE 3: “ENT” KEY SELECTS FIELD TO BE EDITED, AND KEYS
CHANGE FIELD SELECTION FROM NOT MADE TO MADE, “REC” KEY STORES
SELECTION, “CLR” EXITS TO BLANK DISPLAY.
NOTE 4: SELECTIONS ARE MADE, ALL MADE OR AS SELECTED
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
Figure 7−37. Balance Monitor, NOTAR Data
7−58
Reissue 3
Original
NOTAR SOLUTION
<NOT MADE>
F90−146
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
BALANCE MONITOR
SECOND LEVEL
THIRD LEVEL
MAIN ROTOR
BALANCE
CSP−900RFM206A−1
Systems Description
FOURTH LEVEL
FLY 104% GND
PRESS REC
NOTE 1
MAIN ROTOR TRACK
GATHERING TREND
SET XX SPC XX/XX
NOTE 2
NOTAR
BALANCE
TREND SPECTRUM
SET XX COMPLETE
TREND SPECTRUMS
SPECTRUM
FLY HOVER IGE
PRESS REC
NOTE 1
RANDOM SPECTRUM
PRESS REC
BMS FAULT LOG
GATHERING TREND
SET XX SPC XX/XX
NOTE 1
GATHERING RANDOM
NO XX SPC XX/XX
BMS VERSION LOG
NOTE 2
TREND SPECTRUM
SET XX COMPLETE
NOTE 2
RANDOM SPECTRUM
NO XX COMPLETE
FLY 120 KIAS
PRESS REC
NOTE 1
GATHERING TREND
SET XX SPC XX/XX
NOTE 2
TREND SPECTRUM
SET XX COMPLETE
NOTE 1: AUTOMATICALLY STEPS THROUGH ACQUIRING
MEASUREMENTS SPECIFIED FOR THIS REGIME.
NOTE 2: WHEN COMPLETE, THE RESULT IS DISPLAYED
FOR 3 SECONDS AND DISPLAY GOES BACK TO
RANDOM SPECTRUM MENU
NOTE 3: WHEN COMPLETE, THE RESULT IS DISPLAYED
FOR 3 SECONDS AND THE DISPLAY GOES TO THE
NEXT REGIME.
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−147
Figure 7−38. Balance Monitor, Spectrum
Reissue 3
Original
7−59
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
SECOND LEVEL
BALANCE MONITOR
MAIN ROTOR
BALANCE
THIRD LEVEL
MAIN ROTOR TRACK
NOTAR
BALANCE
NOTE 1
BALANCE OK
SPECTRUM
OR
BMS ADVISORY LOG
END OF BMS
ADVISORY LOG
BMS FAULT LOG
DBASE USAGE XXX%
ADVISORIES = XX
NOTE 2
BMS VERSION LOG
BMS OK
OR
END OF BMS
FAULT LOG
BMS MAINTENANCE
NOTE 1: OR VIBRATION DATA
NOTE 2: OR ERROR MESSAGES
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
Figure 7−39. Balance Monitor, BMS Fault Log
7−60
Reissue 3
Original
F90−148
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
BALANCE MONITOR
SECOND LEVEL
CSP−900RFM206A−1
Systems Description
THIRD LEVEL
BMS BOARD P/N
XXXXX-XX
MAIN ROTOR
BALANCE
BMSBP VER XX.XXX
P/N XXXXX-XX
MAIN ROTOR TRACK
NOTAR
BALANCE
BMSBP CHECKSUM
XXXXXXXX
SPECTRUM
BMSOP VER XX.XXX
P/N XXXXX-XX
BMS ADVISORY LOG
BMSOP CHECKSUM
XXXXXXXX
BMS FAULT LOG
BMSBM VER XX.XXX
P/N XXXXX-XX
BMS VERSION LOG
BMSBM CHECKSUM
XXXXXXXX
BMS MAINTENANCE
MAIN ROTOR MODEL
VER XX.XXX
NOTAR MODEL
VER XX.XXX
VIB MONITOR
VER XX.XXX
SPECTRUM SETUP
VER XX.XXX
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−149
Figure 7−40. Balance Monitor, BMS Version Log
Reissue 3
Original
7−61
CSP−900RFM206A−1
Systems Description
TOP LEVEL
BALANCE MONITOR
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
THIRD LEVEL
CLEAR FAULT
LOG
MAIN ROTOR
BALANCE
MAIN ROTOR TRACK
NOTE 1
CLEAR ADVISORY
LOG
NOTAR
BALANCE
CLEAR SPECTRUM
LOG
CLEAR M/R
BALANCE LOG
SPECTRUM
BMS ADVISORY LOG
CLEAR NOTAR
BALANCE LOG
BMS FAULT LOG
CLEAR SETUP
CONFIGURATION
CLEAR ALL LOGS
BMS VERSION LOG
FORMAT DATABASE
AND RESET BMS
BMS MAINTENANCE
NOTE 2
NOTE 1: FOR ALL ``CLEAR'' MENU SELECTIONS, PRESS ENT KEY AND A ``PRESS TO
CLEAR'' MESSAGE WILL BE DISPLAYED. PRESS REC KEY TO CLEAR THE LOG
AND A ``CLEARED OK PRESS ANY KEY'' MESSAGE WILL BE DISPLAYED.
PRESSING ANY KEY WILL RETURN TO THE ``CLEAR LOG MENU''.
NOTE 2: PRESS ENT KEY AND A ``PRESS TO FORMAT AND RESET'' MESSAGE WILL
BE DISPLAYED. PRESS REC KEY TO FORMAT THE DATA BASE AND A ``DBASE
FORMATTED INITIALIZING BMS'' MESSAGE WILL BE DISPLAYED. PRESSING
ANY KEY WILL RETURN TO THE ``CLEAR LOG'' MENU AFTER 30 SECONDS
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
Figure 7−41. Balance Monitor, BMS Maintenance
7−62
Reissue 3
Original
F90−150
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
TOP LEVEL
ENT
AIRCRAFT MONITOR
EXCEEDANCE LOG
CSP−900RFM206A−1
Systems Description
THIRD LEVEL
ENT
TREND LOG
EXCEED LOG XXX
L ENG TORQUE
DATE XX-XX-91
TIME XX:XX:XX
FAULT LOG
PEAK VALUE XXX%
SEC TO PK = XX SEC
IIDS SETUP
DATA LOG NO X
SEC ABV T1 = XX
SEC TO T2 = XX
SEC ABV T2 = XX
SEC TO T3 = XX
SEC ABVT3 = XX
SEC TO T4 = XX
SEC ABV T4 = XX
THE EXCEEDANCE LOG PROVIDES A ``SNAPSHOT” RECORD OF THE PARAMETER DATA AT A
PARTICULAR MOMENT IN TIME. THIS TYPE OF RECORD OCCURS WHENEVER A PARAMETER
EXCEEDANCE IS DETECTED.
NOTE: PRESSING THE
BUTTON WILL TAKE YOU TO THE PREVIOUS HIGHEST MENU LEVEL.
MENU
F90−069
Figure 7−42. Aircraft Monitor, Exceedance Log Menu
Reissue 3
Original
7−63
CSP−900RFM206A−1
Systems Description
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENT
AIRCRAFT MONITOR
EXCEEDANCE LOG
ENT
TREND LOG
TREND LOG XX
LEFT ENGINE
FAULT LOG
DATE
TIME
IIDS SETUP
NP XXX%
T1 XC
TORQUE XX%
NG XX%
EGT XXXC
P0 XXXX FT
OAT XX C
PERFORM MARGIN
L PA CK NG -XX
L PA CK EGT-XX
NG COR FTR XX.X
EGT COR FTR XXX
NOTE: PRESSING THE
BUTTON WILL TAKE YOU TO THE PREVIOUS HIGHEST MENU LEVEL.
MENU
F90−138
Figure 7−43. Aircraft Monitor − Trend Log
7−64
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
TOP LEVEL
CSP−900RFM206A−1
Systems Description
THIRD LEVEL
ENT
AIRCRAFT MONITOR
EXCEEDANCE LOG
TREND LOG
ENT
FAULT LOG
FAULT LOG
L ENG S/N
R ENG S/N
DATE
IIDS SETUP
TIME
IIDS FALT1=X XX
XX, XX
IIDS FALT XX
ACFT FALT=X
SENS FALT=X
BMS FALT=X
LEFT EEC
DSCWD1 =X XX XX
THE FAULT LOG CONTAINS DATA ASSOCIATED WITH EEC
FAULTS AND FAILURES DETECTED IN THE IIDS, BMS, OR
AIRCRAFT TRANSDUCERS/SENSORS. THIS LOG IS RE­
CORDED WHENEVER AN IIDS OR EEC FAULT IS DE­
TECTED. STORAGE IS AVAILABLE FOR 100 FAULT LOGS.
NCFAL1=X XX
NCFAIL2=X XX XX
NCFAL3=X XX
CFAIL=0
RIGHT EEC
DSCWD1=
NOTE: PRESSING THE
BUTTON WILL TAKE YOU
MENU
TO THE PREVIOUS HIGHEST MENU LEVEL.
RIGHT EEC MENU SAME AS
LEFT EEC MENU.
F90−070
Figure 7−44. Aircraft Monitor, Fault Log Menu
Reissue 3
Original
7−65
CSP−900RFM206A−1
Systems Description
TOP LEVEL
AIRCRAFT MONITOR
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
THIRD LEVEL
EXCEEDANCE LOG
A/C NO XXXXXXXX
TREND LOG
ENG INSTALL PWC
IPS INSTALLED
HT/DEFOG INSTAL
ROTOR BRK INSTAL
FAULT LOG
FWD FUEL CAL XXX
AFT FUEL CAL XXX
IIDS SETUP
TOP LVL SFTWR PN
XXXXXXXXXXXX
OPER SFTWR PN
XXXXXXXXXXXX
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MAINT SFTWR PN
XXXXXXXXXXXX
BMSBM SFTWR PN
XXXXXXXXXXXX
BMSOP SFTWR PN
XXXXXXXXXXXX
SETUP DATA ID
XXXXXXXX
BMSBP SFTWR PN
XXXXXXXXXXXX
CFG DAT MM-DD-YY
CFG TIM HR:MN:SE
MENU
F90−141
Figure 7−45. Aircraft Monitor − IIDS Setup
7−66
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOP LEVEL
SECOND LEVEL
Systems Description
THIRD LEVEL
NOTE 2
NOTE 1
FUEL CALIBRATION
CSP−900RFM206A−1
SET CAL CODE
FWD FUEL CAL<XXX>
AFT FUEL CAL <XXX>
NOTE 1
DO CALIBRATION
AIRCRAFT READY?
CRUISE ATTITUDE?
NOTE 3
FWD FUEL CAL XXX
AFT FUEL CAL XXX
NOTE 1: PRESS “ENT” FOR MORE THAN 4 SECONDS TO ENTER
FUNCTION, THIRD LEVEL MENU APPEARS.
NOTE 2: “ENT” SELECTS DIGITS TO BE EDITED, AND KEYS
CHANGE SELECTED DIGITS, “REC” KEY STORES
SELECTION, “CLR” EXITS TO BLANK DISPLAY.
NOTE 3: PRESS “ENT” FOR MORE THAN 4 SECONDS COMMANDS
CALIBRATION. IIDS WITH CAL CODES AFTER
CALIBRATION COMPLETE. “REC” CHANGES CODE TO
CALCULATED VALUE. PRESS ``MENU'' TWICE TO
RETURN TO TOP LEVEL
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
NOTE: TO MOVE HORIZONTALLY ( → ) TO THE NEXT LOWER LEVEL - PRESS
ENT
F90−152
Figure 7−46. Fuel Calibration
Reissue 3
Original
7−67
CSP−900RFM206A−1
Systems Description
TOP LEVEL
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
SECOND LEVEL
NOTE 1
SET ENGINE PARM
LNG COR FCTR <XX.X>
LEGT CORFCT <XX.X>
NOTE 1
RNG COR FCTR <XX.X>
REGT CORFCT <XX.X>
NOTE 1: “ENT” SELECTS DIGITS TO BE EDITED, AND KEYS
CHANGE SELECTED DIGITS, “REC” KEY STORES
SELECTION, “CLR” EXITS TO BLANK DISPLAY.
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
F90−140
Figure 7−47. Set Engine Parameters
TOP LEVEL
SECOND LEVEL
NOTE 1
SET TIME/DATE
TIME <HH:MM>
DATE MM-DD-YY
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
NOTE 1.: ``ENT'' KEY SELECTS FIELD TO BE SET (MINUTE,
HOURS, DAY, MONTH, YEAR) AND SELECTED FIELD
BLINKS, AND KEYS INCREMENT/DEINCRE­
MENT DIGIT VALUE, ``REC'' KEY CHANGES TIME
MENU
AND DATE TO SELECTED VALUES
F90−151
Figure 7−48. Set Time/Date
7−68
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
S E C T I O N VIII
HANDLING, SERVICING
AND MAINTENANCE
TABLE OF CONTENTS
PARAGRAPH
PAGE
8-1. Hoisting, Lifting and Jacking . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-1
8-2. Towing and Moving . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-1. Helicopter Towing and Ground Handling . . . . . . . . . . . . . . . . . . . . .
8-1
8-4
8-3. Parking and Storage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-2. Helicopter Tiedowns and Covers . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-3. Helicopter Grounding . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-4
8-6
8-8
8-4. Access and Inspection Provisions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-4. Access Methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-5. Nose Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-6. Left Side Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-7. Right Side Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-8. Top View Access Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-9. Bottom View Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-10. Stabilizers Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-11. Cabin Floor Interior Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-12. Pedestal Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-13. Fan Assembly Access Panels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-10
8-11
8-12
8-13
8-14
8-15
8-16
8-17
8-18
8-19
8-20
8-5. Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-14. Servicing Points . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 8-1. Acceptable Fuels . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 8-2. Servicing Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-15. Fuel System Range Extender Gravity Filler Port . . . . . . . . . . . . .
Figure 8-16. Hydraulic System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-17. Main Transmission Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-18. Rotor Brake . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-19. Engine Oil System - Servicing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-21
8-21
8-22
8-22
8-25
8-27
8-29
8-30
8-32
8-6. Aircraft Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-33
8-7. Cockpit Door Removal . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-34
Reissue 3
Original
8−i
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PARAGRAPH
PAGE
Figure 8-20. Cockpit Door Attachment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8-35
8-8. Cabin Seats: Removal/Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-21. Cabin Passenger Seat Attachment . . . . . . . . . . . . . . . . . . . . . . . . . .
8-36
8-36
8-9. Copilot Flight controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-22. Copilot Pedals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-37
8-37
8-10. Engine Charts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-23. EGT Vs Time - All Conditions Except Starting . . . . . . . . . . . . . . .
Figure 8-24. EGT Vs Time - Starting . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-25. Power Turbine (NP) Speed Vs Time . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-26. Compressor Turbine (NG) Speed Vs Time . . . . . . . . . . . . . . . . . . . .
Figure 8-27. Engine Overtorque Limits - All Conditions . . . . . . . . . . . . . . . . . .
8-38
8-38
8-39
8-39
8-40
8-40
8-11. Special Operational Checks and Procedures . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine NP Overspeed Check Procedure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Hydraulic System Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
VSCS Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Wet Engine Motoring Run . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Dry Engine Motoring Run . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Out/Low Rotor Warning Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Engine Wash . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-28. Engine Wash Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Manual Engine Shutdown Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Manual Engine Start Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Autorotation RPM Check . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Resetting IIDS Time/Date . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 8-29. Set Time/Date . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
8-41
8-41
8-42
8-42
8-43
8-43
8-44
8-44
8-46
8-47
8-48
8-49
8-50
8-50
8−ii
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
SECTION VIII
HANDLING, SERVICING AND
MAINTENANCE
8−1.
HOISTING, LIFTING AND JACKING
CAUTION
8−2.
Hoisting, lifting, and jacking of the helicopter shall only be
performed with the proper equipment and tools as specified in the
MD900 Rotorcraft Maintenance Manual. Failure to follow the
specified procedures will result in damage to aircraft components.
TOWING AND MOVING
Moving the helicopter on prepared surfaces is accomplished by mounting ground
handling wheels to fittings located on the landing gear skid tubes.
The ground handling wheel set is used for moving the MD Explorer by hand and
for towing. The wheels are manually lowered with a detachable jack handle, and
are held in the down position by a mechanical lock. The ground handling wheel
set is equipped with a tow bar attach fitting.
Helicopter Manual Moving:
Ensure all stress panels listed in Figure 8-11 are installed.
CAUTION
Airframe structure damage can occur if stress panels are not in
place before moving helicopter.
NOTE: The wheel set attaches at four points, two inboard and two outboard, on the skid
assemblies.
A ``T” handle is strapped to the skid tubes and extends out, to pull the wheels
to and from the helicopter.
Position wheel set over skid tubes and roll wheel set forward.
NOTE: The wheel set can be installed in either direction, depending on jack handle
position.
Attach wheel set to attach points on skid tubes.
Hold tail up while lowering ground handling wheels.
Jack hydraulic ram which forces wheels down and skids up.
Reissue 3
Original
8−1
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
When the jack is extended, a mechanical safety latch automatically snaps into
position, to prevent the wheels from going up in the event of loss of hydraulic
pressure.
CAUTION
Operators and maintenance personnel should avoid lead−lag loads
in excess of 25 pounds at the tip of the main rotor blades.
Excessive lead-lag load applied to the main rotor blades during ground handling
can result in damage to the damper assembly.
Manually move helicopter on ground handling wheel set by balancing tailboom
and pushing on rear fuselage portion of airframe.
CAUTION
When ground handling helicopter do not lift main rotor blades to
clear objects. The main rotor should be rotated to clear objects.
To prevent rotor component damage, the main rotor hub deflection
for a non−operating rotor is not to exceed four feet up, maximum.
Measurement to be taken from static rest.
Helicopter Towing:
The towbar is equipped with caster wheels and is designed for use with the
ground handling wheels and allows the helicopter to be moved by one person.
The towbar does not interfere with equipment that may be hung under the heli­
copter
Ensure all stress panels listed in Figure 8-11 are installed.
CAUTION
Airframe structure damage can occur if stress panels are not in
place before moving helicopter.
Raise helicopter up with wheel set.
Position caster wheels, to straddle, over front skid tubes.
Attach nylon strap under skid tubes and ratchet skid tubes into rubber cups.
Attach tow bar to a power unit.
CAUTION
Do not tow helicopter at speeds over 5 mph.
When ground handling helicopter do not lift main rotor blades to
clear objects. The main rotor should be rotated to clear objects.
To prevent rotor component damage, the main rotor hub deflection
for a non−operating rotor is not to exceed four feet up, maximum.
Measurement to be taken from static rest.
Avoid sudden stops and starts.
8−2
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Avoid short turns, which could cause helicopter to turn over.
CAUTION
A safe minimum turning radius is approximately 20 feet.
Allow inside wheel to turn (not pivot) while helicopter is being turned.
Helicopter Transport:
The heli-porter is designed for the MD Explorer with the use of a towing tractor
or vehicle.
The heli-porter is a welded tubular steel frame with dual pneumatic swivel
caster on the front and rear. The platform is a grated walkway with hold down
safety straps for the landing gear. The heli-porter has a hand brake to the rear
tires and has a 10,000 lb (4540 Kg) capacity.
Ensure all stress panels listed in Figure 8-11 are installed.
CAUTION
Airframe structure damage can occur if stress panels are not in
place before moving helicopter.
Land or hoist helicopter (Ref. RMM, Section 07-10-00) on heli-porter platform.
Attach safety hold-down straps to skid tubes.
Release heli-porter hand brake.
CAUTION
CAUTION
When ground handling helicopter do not lift main rotor blades to
clear objects. The main rotor should be rotated to clear objects.
To prevent rotor component damage, the main rotor hub deflection
for a non−operating rotor is not to exceed four feet up, maximum.
Measurement to be taken from static rest.
Do not tow helicopter at speeds over 5 mph. A safe minimum turning
radius is approximately 20 feet.
Attach heli-porter hook-up to a tow vehicle.
Reissue 3
Original
8−3
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
TOW BAR
GROUND
HANDLING
ATTACH POINTS
VIEW ROTATED
HELI-PORTER
SKID TUBE
F90−086
Figure 8−1. Helicopter Towing and Ground Handling
8−3.
PARKING AND STORAGE
Helicopter tiedowns and covers:
Covers and tiedowns (Ref. Figure 8-2) are provided to shield the MD Explorer
from inclement weather conditions and other outside environmental factors that
could cause FOD damage while the helicopter is parked, moored, or while in
storage.
NOTE: The decision to use protective covers and tiedowns is determined by the
prevailing weather conditions, length of storage/parking, and location.
Forward and aft tiedowns
Each tiedown (Ref. Figure 8-2) has a quick connect fitting with a streamer
attached ``REMOVE BEFORE FLIGHT”. Two aft tiedown straps are to
be attached to the upper aft fitting. Two separate upper forward tiedowns
attach to the forward fuselage. Additional lower fore and aft tiedown attach
points are located on left and right side of helicopter.
Blade tiedowns
Blade tiedowns (Ref. Figure 8-2) are socks, which fit over the blade tip, with
or without the blade covers installed.
Each blade tiedown is fitted with a generous length of rope which can be
tied down at any convenient spot.
Upper deck cover
The upper deck cover (Ref. Figure 8-2), encloses the NOTAR inlet, particle
separator inlets and exhaust stacks.
8−4
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Attach cover, at forward corners to snap-head screws placed in existing screw
holes on lower edge of particle separator inlet.
Attach cover, at rear corners with similar snaps, or with a strap going under­
neath the tailboom where it meets the fuselage.
NOTAR boom cover
The boom cover (Ref. Figure 8-2) is a tubular cover made of nylon. Attach
boom cover to thruster using side-release buckles.
NOTAR thruster cover
The MD Explorer thruster cover (Ref. Figure 8-2) encloses the thruster cone
and chokes tightly around the base near the trailing edge of the horizontal
stabilizor.
Position cover on thruster.
Tighten cover with strap assembly.
Pitot tube cover
The pitot cover (Ref. Figure 8-2) is vinyl and reinforced with galvanized steel
staples at stress points.
A bright red warning streamer, ``REMOVE BEFORE FLIGHT” attaches
to the bottom edge of the cover
Attach pitot cover around pitot base.
Bubble cover
The MD Explorer bubble cover (Ref. Figure 8-2), encloses the entire canopy,
including the windshield, front and rear doors and windows.
The cover, attaches at four points.
The cover, is color-coded, with swatches sewn in the corners, for ease of instal­
lation. Red = Left, Green = Right.
Attach upper rear corners to snap-head screws placed in existing screw holes
on lower edge of particle separator inlet.
Attach straps at lower rear corners to rear struts.
Tighten special rope in top and bottom hems, to insure a guarantee against
wind chaffing.
A large bright red pocket is sewn in the cover, for the temperature probe.
Reissue 3
Original
8−5
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FORWARD UPPER TIEDOWN
AFT UPPER TIEDOWN
FORWARD LOWER TIEDOWN
(IF INSTALLED)
AFT LOWER TIEDOWN
(IF INSTALLED)
BLADE TIEDOWN
PITOT TUBE COVER
ROTOR HUB COVER
THRUSTER COVER
ENGINE AREA COVER
UPPER DECK COVER
BOOM COVER
BLADE COVER
BUBBLE COVER
F90−073A
Figure 8−2. Helicopter Tiedowns and Covers
8−6
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Rotor hub cover
The MD Explorer rotor hub cover (Ref. Figure 8-2) overlaps with the blade
covers and the engine area cover to insure complete protection for the entire
main rotor system.
Position cover over top of rotor hub.
Attach cover with buckles under each blade.
Tuck lower part of cover into the aperture beneath the rotor.
Engine area cover
The engine area cover is similar and does the same job as the upper deck
cover, except that it also encloses the fan inlet.
Blade covers - standard
Blade covers (Ref. Figure 8-2) can be installed from the ground.
Tighten covers at blade root with attached straps and buckles.
The small opening at the blade tip bottom allows attachment of tiedown ropes.
Blade covers - cold weather
The MD Explorer cold weather blade covers are similar to the standard blade
covers, but are fitted with full length zippers and heater hose boots near
the blade root.
Helicopter Parking
The decision to use protective covers and tiedowns is determined by the prevailing
weather conditions, length of parking, and location.
Normal Conditions
NOTE: Tie down rotor blade(s) whenever helicopter is parked in an area subject to
turbulent or gusting winds to prevent rotor windmilling. The maximum blade tie
down load is when the blade tip just begins to deflect downward.
Install pitot cover.
Close and secure all doors, windows and access panels.
Statically ground helicopter if possible.
Turbulent/Gusting Wind Conditions
CAUTION
Tie down all blades in winds of 45 knots or more to prevent
excessive flapping and possible flexbeam damage.
NOTE: Maximum demonstrated wind speed for starting and stopping the rotor is 50
knots.
Reissue 3
Original
8−7
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
If possible, park helicopter into the prevailing wind and secure in accordance
with normal parking conditions.
Statically ground helicopter (Ref. Figure 8-3).
GROUNDING JACK
(2 LOCATIONS)
CABLE PLUG
F90−080
Figure 8−3. Helicopter Grounding
Helicopter Storage:
Install protective covers as necessary (Ref. Figure 8-2 ) to prevent entry of blow­
ing dust, water, freezing rain, snow and/or foreign objects into the helicopter
during ground storage.
Maintain full fuel cell to reduce condensation in the cell.
Ensure drain holes are free of debris and kept open during storage period.
Store helicopter in hangar, if space allows.
Statically ground helicopter (Ref. Figure 8-3).
Flyable Storage
Flyable storage will maintain a stored MD Explorer in an operable condition.
If daily use is impractical, the following procedures will keep the helicopter in
flyable condition. At regular intervals inspect helicopter. Date and type of storage
must be recorded in helicopter records.
Perform engine run-up, at least once every five days.
Perform pre-flight inspection, at least once every seven days.
Inspect helicopter and treat for corrosion control.
Inspect static ground wires, blade tiedowns and mooring devices at regular inter­
vals.
Inspect tiedowns immediately after winds exceeding 35 knots.
Enter type of storage and date helicopter was placed in storage, in helicopter
records.
8−8
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
High Wind Conditions - Helicopter Mooring:
When severe storm conditions or wind velocities higher than 40 knots are forecast,
helicopter should be hangared or evacuated to a safe area. If the helicopter must
be parked in the open during high winds, comply with the following.
CAUTION
Structural damage can occur from flying objects during high wind
conditions. Helicopter should be hangared or evacuated to a safe
weather area when wind conditions above 75 knots are expected.
If a paved ramp with tiedown rings are available, park helicopter headed in
direction from which highest forecast winds are expected.
Secure helicopter to ramp tiedowns using forward and aft tiedowns (Ref.
Figure 8-2).
If a paved ramp with tiedown rings are not available, park helicopter on an
unpaved parking area, headed in the direction from which highest forecast winds
are expected.
Install blade tiedowns.
CAUTION
Tiedown rotor blades, whenever helicopter is parked, to prevent
rotor damage from blade flapping as a result of air turbulence from
other aircraft or wind gusts. The maximum blade tie down load
is when the blade tip just begins to deflect downward.
Install engine area cover (Ref. Figure 8-2), and pitot cover.
Fill fuel cell, if possible.
After winds subside, inspect helicopter carefully for damage which may have
been inflicted by flying objects.
Return to service:
Flyable Storage Depreservation and Activation
Remove protective covers and tiedowns.
Clean helicopter as necessary.
Open all doors and ventilate helicopter.
Record date helicopter was prepared for service in helicopter records.
Remove static ground wire installed for storage.
Perform preflight checks.
Reissue 3
Original
8−9
CSP−900RFM206A−1
Handling Servicing
and Maintenance
8−4.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ACCESS AND INSPECTION PROVISIONS
Various doors, covers, panels, and fairings are located through out the airframe
to provide access for inspection, maintenance, and servicing. External and internal
doors, covers, panels and fairings are shown in Figure 8-4 thru Figure 8-13. Each
door, cover, panel, and fairing has a letter and a number designator. Each figure
is directly related to a corresponding table which lists a reference designator, panel
name, accessible item, access method and fastener type.
Reference Designator:
The number indicates the nearest attaching fuselage station.
The letter indicates the location:
(N) Nose
(L) Left Side
(R) Right Side
(T) Top Side
(B) Bottom Side
(A) Cabin Floor (interior access)
(S) Stabilizer
(P) Pedestal (interior)
(F) Fan Assembly (interior)
A combination of two letters may be used to help identify a door, cover, panel
or fairing:
(FR) floor right
(FL) floor left
L and R will indicate doors, panels, and covers at the same station location:
F(L/R)160.0.
Removal and Installation Methods:
Removal or installation of doors, covers, panels, and fairings are described by
a method listed in a table with a supporting illustration. The type of fastener
and quantity used to remove or secure the door, cover, panel, and fairing is listed.
8−10
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CAMLOC
KEYLOC
Handling Servicing
and Maintenance
HINGE
LATCH
UNLOCKED
LOCKED
1/4
TURN
UNLOCKCOUNTERCLOCKWISE
LOCK-CLOCKWISE
UNLOCKCOUNTERCLOCKWISE
LOCK-CLOCKWISE
ROTATES 180°
TO UNLOCK
PUSH HERE
TO UNLOCK
LATCH
CAMLOC
UNLOCKED
LOCKED
LOCKED
SLEEVE BOLT
UNLOCKED
1/4
TURN
PUSH TO
UNLOCK
LEVER ACTION HANDLE
HINGE PIN
PUSH TO
LOCK
CAMLOC
SCREW
PIN
PULL TO RELEASE
DOOR PINS
BOLT
LATCH
UNLOCK-ONE ACTION
LOCK-TWO ACTIONS
1 PUSH
HOOK-1
PULL
2 PULL
PUSH-2
LIFT
STRUT
TURN AND LOCK
LOCKED
CLOSED
CAMLOC
UNLOCKED
PULL OFF
HERE
LIFT
HERE
9G06-008
Figure 8−4. Access Methods
Reissue 3
Original
8−11
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
N80
N82
N106
9G06-001
Removal and Installation
Item
No.
Name
Permits Access To
N80
Nose Door
Pitot − Static System, Battery
N82
Panel
Landing Light, Flight Control Rods
Avionics Cooling Fan, Wire Harness,
External Power Box
N106 Panel
Quantity
Reissue 3
Original
Method
Ref
Figure 8−4
2
1
Latch
Keyloc
B
A
18
Screw
L
30
Screw
L
Figure 8−5. Nose Access Panels
8−12
Type
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
L220
CSP−900RFM206A−1
Handling Servicing
and Maintenance
L260
L270
L210
L155
L262
L166
L109
L210
NACA INLET
INSTALLATION
L107
9G06-002A
Removal and Installation
Item
No.
Name
Permits Access To
L107
Crew Door Copilot
Instrument Panel, Pedestal Console
L109
Access Panel Assembly
Avionics, LH
Electrical, Avionics, Flight Controls,
Static System Drain Valve
L155
Forward Access Door Assembly, LH
L166
L210
Quantity
Type
Method
Ref
Figure 8−4
1
1
1
1
14
Lever Action Handle
Hinge Pin / Pin
Strut End
Keyloc
Camloc
H
J, K
T
A
B
Passenger Door, LH
Main Transmission Access, Flight Control Actuators, Hydraulic Hand Pump,
System 1 Hydraulic Manifold/Reservoir
Passenger and Cargo Compartment
3
5
2
1
Latch or
Camloc
Hinge
Lever Action Handle
C
E or U
D
H
Xmsn Access Door Assembly, LH
Main Transmission Access, Engine
Reduction Gearbox Housing
3
5
2
Latch or
Camloc
Hinge
C
E or U
D
L210
Transmission Access
Door Assembly, LH
UPPER W/ NACA
INLET
Main Transmission Access, Engine
Reduction Gearbox Housing
2
5
Hinge
Camloc
D
E
L210
Transmission Access
Door Assembly, LH
LOWER W/ NACA
INLET
Main Transmission Access, Engine
Reduction Gearbox Housing
7
Camloc
E
L220
Engine Air Inlet Panel Assembly, LH
Inlet, Engine Compressor
25
Fastener Sleeve Bolt
G
260
Engine Cowling Assembly, LH
Engine, Engine Controls
10
Fastener Sleeve Bolt
G
L262
Baggage Compartment
Door
Baggage Compartment,
behind trim panels; Engine EEC’s, Wire
Harness, ECS Bleed Air Lines, Fuel
Lines, Drain Lines, Electrical Load
Center, Engine Fire Extinguishing
Bottles (optional)
1
Lever Action Handle
H
L270
Exhaust Ejector Cowl Assembly, LH
Engine Exhaust
Machine Screw
L
18
Figure 8−6. Left Side Access Panels
Reissue 3
Original
8−13
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
R260
R220
R210
R270
R155
R107
R166
R210
NACA INLET
INSTALLATION
R185
R158
R128
R109
9G06-003A
Removal and Installation
Item
No.
Name
Permits Access To
R107
Crew Door Pilot
Instrument Panel, Pedestal Consol
R109
APU/EPR Door
Auxiliary / External Power Receptacle
R128
Avionics Access Panel
R155
Forward Access Door Assembly, RH
R158
Fuel Cap and Adapter
Electrical, Avionics, Flight Controls,
ECS Bleed Air Lines, Static System
Drain Valve
Main Transmission Access, Flight
Control Actuators, System 2 Hydraulic
Manifold/Reservoir
Fuel Filler Neck
R166
Passenger Door, RH
R185
Quantity
1
1
1
1
1
14
Type
Lever Action Handle
Pin Assembly
Strut
Camloc
Key Loc
Camloc
Method
Ref
Figure 8−4
H
J, K
T
E
A
B
3
5
2
1
Latch or
Camloc
Hinge
Turn and Lock
Passenger and Cargo Compartment
1
1
Lever Action Handle
Release Pin
H
R
Fuel Drain Access Panel
Assembly
Fuel Sump Drain Control, Cables
1
Camloc
N
R210
Xmsn Access Door Assembly, RH
Main Transmission Access, Engine
Reduction Gearbox Housing
3
5
2
Latch or
Camloc
Hinge
C
E or U
D
R210
Transmission Access
Main Transmission Access, Engine
Door Assembly, RH
Reduction Gearbox Housing
UPPER W/ NACA INLET
2
5
Hinge
Camloc
D
E
R210
Transmission Access
Door Assembly, RH
LOWER W/ NACA
INLET
Main Transmission Access, Engine
Reduction Gearbox Housing
7
Camloc
E
R220
Engine Air Inlet Panel Assembly, RH
Inlet, Engine Compressor Section
25
Sleeve Bolt
G
R260
Engine Cowl
Assembly, RH
Engine, Engine Controls
11
Sleeve Bolt
G
R270
Exhaust Ejector Cowl Assembly, RH
Engine Exhaust
19
Machine Screw
L
Figure 8−7. Right Side Access Panels
8−14
Reissue 3
Original
C
E or U
D
S
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Handling Servicing
and Maintenance
T292
TR218
T240
T155
T220
TL218
9G06-009
Removal and Installation
Item
No.
Name
Permits Access To
Quantity
T155
Forward Fairing Assembly Swashplate
Hydraulic Servo Actuators,
Swashplate, Mixer
19
4
TL118
Oil Dipstick Hand
Hold, LH
Engine Oil Level and Filler
TR118 Oil Dipstick Hand
Hold, RH
Engine Oil Level and Filler
T220
Aft Fairing Assembly
Swashplate
Mast Support, Transmission,
Flight Controls, ECS, Engine
Oil Level and Filler
T240
Upper Inlet Duct Assembly
Fan driveshaft, air inlet to fan
T292
Upper Tailboom Fairing Assembly
Required Panel Removal T240,
L270 and R270
Type
Method
Ref
Figure 8−4
Screw
Bolt
L
M
1
2
Hinge
Camlock
Q
E
1
2
Hinge
Camlock
Q
E
58
4
Screw
Bolt
L
M
19
24
Screw
Bolt
L
M
7
Screw
L
Figure 8−8. Top View Access Panel
Reissue 3
Original
8−15
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
B178
B142
B230
9G06-005
Item
No.
Removal and Installation
Name
Permits Access To
Quantity
Type
Method Ref
Figure 8−4
B142 Access Panel Assembly Center
Throttle Interconnect Cable, RH
Collective
14
Screw
L
B178 Access Panel Assembly Sump
Fuel Sump Drain Valves
22
Screw
L
B230 Aft Crosstube Cover
Assembly
Landing Gear Crosstube Aft
30
Screw
L
Figure 8−9. Bottom View Access Panels
8−16
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Handling Servicing
and Maintenance
S6
SR5
SL5
SR7
SL7
S4
SR3
SR1
SL1
SL3
S2
9G06-004
Removal and Installation
Item
No.
Name
Permits Access To
S2
Lower Tailboom/
Thruster Fairing
Assembly
Horizontal Stabilizer Mount Fitting
Stationary Thruster Mounting
S4
Thruster End Cover
Attachment Bolts For Rotating
Thruster
S6
Leading Edge Cover
Center
SL1
Upper Tailboom/
Thruster Fairing Assembly, Left Side
SL3
Quantity
Type
Method
Ref
Figure 8−4
22
Screw
L
8
Screw
L
10
Screw
L
21
Screw
L
Outboard Fairing AsVertical Stab Torque Tube, Control
sembly, LH (Endplate) Rod Electrical Wiring, Position Light
14
Screw
L
SL5
Center Access Cover,
LH (Horizontal Stabilizer)
Wiring
10
Screw
L
SR1
Upper Tailboom/
Thruster Fairing
Assembly Right Side
Horizontal Stabilizer Mount Fitting
Stationary Thruster Mounting
21
Screw
L
SR3
Outboard Fairing AsVertical Stab Torque Tube, Control
sembly, RH (Endplate) Rod Electrical Wiring, Position Light
14
Screw
L
SR5
Center Access Cover
(Horizontal Stabilizer)
Wiring
10
Screw
L
SR7 Access Cover
RH VSCS Actuator
10
Screw
L
SL7
LH VSCS Actuator
10
Screw
L
Access Cover
Horizontal Stabilizer Mount Fitting
Stationary Thruster Mounting
Figure 8−10. Stabilizers Access Panels
Reissue 3
Original
8−17
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AR138
AR155
AR230
AR165
AR250
AR129
A235
AL138
AL230
AL129
AL155
A160
AL165
A170
A217
AL250
9G06-010
NOTE: ALL PANELS ARE STRESS PANELS.
Item
No.
A160
A170
A217
A235
AL129
AL138
AL155
AL165
AL230
AL250
AR129
AR138
AR155
AR165
AR230
AR250
Name
Permits Access To
Cabin Floor Forward
Panel Assembly
Cabin Floor Center
Panel Assembly
Cabin Floor Aft Panel
Assembly
Baggage Floor Center
Panel
Cockpit Outboard Left
Floor Panel
Cockpit Floor Left
Access Panel
Cabin Floor Left Forward Access Cover
Cabin Floor Left Outboard Panel
Cabin Floor Left Aft Access Cover
Baggage Floor Left
Outboard Panel
Cockpit Outboard Right
Floor Panel
Cockpit Floor Right
Access Panel
Cabin Floor Right Forward Access Cover
Cabin Floor Right Outboard Panel
Cabin Floor Right Aft
Access Cover
Baggage Floor Right
Outboard Panel
Removal and Installation
Method Ref
Quantity
Type
Figure 8−4
Fuel Cell
69
Screw
L
Fuel Cell
89
Screw
L
Fuel Cell Aft Vent Rollover Valves
75
Screw
L
Crossfeed Valve, Condenser Fans, Condenser
64
Screw
L
LH Collective Stick Socket, Wire Harness, LH
Static Port
Flight Control Tubes, Cyclic Bellcrank
Left Forward Fuel Vent Valve, Fuel Cell
30
1
24
1
12
Screw
Bolt
Screw
Bolt
Screw
L
M
L
M
L
Fuel Cell Frangible Valve, Wire Harness
76
Screw
L
Left Aft Fuel Vent Valve, Fuel Cell
13
Screw
L
Fuel Tee Fittings, Fuel Pressure Switch Drain
Tubing, Fuel Hose Shrouds, Fuel Catch Can
Fire Overheat Bleed Air Leak Control, Wire
Harness, RH Static Port
Flight Control Tubes, Bellcranks, Throttle
Cables
Right Forward Fuel Vent Valve, Fuel Cell
25
4
34
1
35
Screw
Bolt
Screw
Bolt
Screw
L
M
L
M
L
12
Screw
L
Fuel Cell Frangible Valve, Heat/Defog Bleed
Air Line, Fire Overheat Bleed Air Leak Detector
Right Aft Fuel Vent Valve, Fuel Cell
76
Screw
L
13
Screw
L
Fuel Tee Fittings, Fuel Pressure Switch Drain
Tubing, Fuel Hose Shrouds, ECS Tubing,
Strobe Power Supply, Fuel Catch Can
25
4
Screw
Bolt
L
M
Figure 8−11. Cabin Floor Interior Access Panels
8−18
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Handling Servicing
and Maintenance
PR120
PL120
9G06-012
Removal and Installation
Item
No.
Name
Permits Access To
Quantity
Type
Method
Ref
Figure 8−4
PL120 Panel
Wire Harness, Forward Interconnect
Panel (Relays), Ground Modules
9
Camloc
U
PR120 Panel
Wire Harness, Forward Interconnect
Panel (TB2, TB3,TB4)
9
Camloc
U
Figure 8−12. Pedestal Access Panels
Reissue 3
Original
8−19
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
F4
F3
F5
REF. STATOR
F6
F7
F9
REF. FAN SUPPORT AND
HOUSING
F8
F2
F1
9G06-013
Removal and Installation
Item
No.
Name
Permits Access To
Quantity
Type
Method
Ref
Figure 8−4
6
Screw
L
19
14
Screw
Bolt
L
M
F1
Anti−Torque Drive Shaft Fan Drive Shaft
Cover
F2
Anti−Torque Lower Inlet
Duct Assembly
F3
Anti−Torque Fan FairFan Assembly, Fan Driveshaft Couing/Center Body Assem- pling, Support Housing, Fan Balance
bly
Monitor System Magnetic Pickup and
Accelerometer
19
Screw
L
F4
Anti−Torque Middle Inlet Fan Assembly Plenum air Inlet
Duct Assembly
4
19
Screw
Bolt
L
M
F5
Anti−Torque Fan Upper
Duct Assembly
Plenum Air Inlet, Upper Stator Blades
attached
24
Screw
L
F6
Upper Center Diffuser
Upper Stator Blades attached
24
Screw
L
F7
Lower Center Diffuser
Fan Assembly and Diverter, Lower
Stator Blades attached
20
Screw
L
F8
Lower Access Panel As- Diverter
sembly
4
Latch
P
F9
Anti−Torque Fan Lower
Duct Assembly
18
Screw
L
Plenum Fan Assembly
Fan Assembly and Diverter, Fan
Control Linkage
Figure 8−13. Fan Assembly Access Panels
8−20
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
8−5.
CSP−900RFM206A−1
Handling Servicing
and Maintenance
SERVICING
General:
Servicing includes replenishment of fuel, changing or replenishment of oil, and
other such maintenance functions (Ref. RMM, Section 12-00-00).
The locations of servicing points are shown in Figure 8-14.
Engine, transmission and hydraulic servicing materials and capacities are shown
in Table 8-2. A complete listing of servicing materials may be found in the RMM,
Section 12-00-00.
8
9
1
2
3
10
7
5
11
6
9G12-002
4
1.
1.
2.
3.
4.
5.
ECS - AIR CONDITIONER REFRIGERANT
ECS − AIR CONDITIONER SYSTEM OIL
ECS − COMPRESSOR REDUCTION GEARBOX OIL
FUEL SYSTEM − FUEL
HYDRAULIC SYSTEM − MANIFOLD/RESERVOIR HYDRAULIC FLUID
LANDING GEAR − DAMPER FLUID
6.
TRANSMISSION & DRIVE SYSTEM − MAIN TRANSMISSION LUBRICATING OIL
7. POWERPLANT − ENGINE LUBRICATING OIL
8. POWERPLANT − ENGINE WASH SOLUTION
9. ROTOR BRAKE − HYDRAULIC FLUID
10. POWERPLANT − FUEL CATCH CAN
Figure 8−14. Servicing Points
Reissue 3
Original
8−21
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Capacities - Fuel System (Standard):
JET A: 1014 lb; 460 kg; 149 U.S. gal; 564L total capacity
994 lbs; 146.2 U.S. gal; 553L useable
JET B: 969 lbs; 440 kg; 149 U.S. gal; 564L total capacity
950 lbs; 146.2 U.S. gal; 553L useable
Capacities - Fuel System (Range Extender):
JET A: 1097 lb; 498 kg; 161.3 U.S. gal; 611L total capacity
1078 lbs; 158.5 U.S. gal; 600L useable
JET B: 1048 lb; 476 kg; 161.3 U.S. gal; 611L total capacity
1030 lbs; 158.5 U.S. gal; 600L useable
Table 8−1. Acceptable Fuels
NOTE: For additional information on fuels, refer to Pratt and Whitney 206A maintenance
Manual.
FUEL TYPE
USA
SPECIFICATION
CANADA
UK
FRENCH
NATO
Kerosene:
Jet A, A-1, A-2**
JP8*
ASTM D1655
MIL-T-83133
CGSB
3.23-M86
AVTUR
DERD 2453*
DERD 2494*
AIR 3405D
F-34
F-35
Wide Cut:
Jet B
JP4*
ASTM D1655
MIL-T-5624
CGSB
3.22-M86
AVTAG
DERD 2454*
DERD 2486*
AIR 3407B
F-40
MIL-T-5624
CGSB
3.GP-24Ma
AVCAT
DERD 2452*
DERD 2498*
AIR 3404C
F-43
F-44
High Flash:
JP5*
PRC
RP-3
* Contains fuel system icing inhibitor (FSII). For JP-8, MIL-T-83133C allows two grades. The grade meeting NATO code F-34 has FSII
while the grade meeting code F-35 has no FSII without prior agreement.
** For Jet A-2 conforming to CAN/CGSB 3.23-M86 is acceptable for use, provided the restrictions regarding flash and freezing points are
strictly observed.
Table 8−2. Servicing Materials
Specification
Material
Manufacturer
1. Engine - Total Capacity 1.34 U.S. Gal (1.12 Imp Gal; 5.12 L)
NOTE: The mixing of different oil brands is not approved.
MIL-PRF-23699
Aero Shell Turbine Oil 500
Shell Oil Co.
50 W. 50th St
New York, NY 10020
Shell Canada Products Ltd.
1500 Don Mills Road
Don Mills, Ontario
Canada M3B 3K4
Shell International Petroleum Co.
Shell Centre
London, SE1 7NA
England
8−22
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Specification
MIL-PRF-23699
Material
Castrol 5000
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Manufacturer
Castrol Canada, Inc.
3660 Lakeshore Blvd. West
Toronto, Ontario
Canada M8W 1P2
Castrol Specialty Products Div.
16715 Von Karman Ave.
Suite 230
Irvine, CA 92714-4918
Castrol (U.K.) Ltd.
Burmah House
Pipers Way
Swindon, Berkshire
SN3 1RE England
Exxon Turbo Oil 2380
Exxon Turbo Oil 2525
Exxon International Co.
200 Park Avenue
Florham Park, NJ 07932-1002
Esso Petroleum Canada
55 St. Clair Avenue West
Toronto, Ontario
Canada M5W 2J8
Exxon Co.
P.O. Box 2180
Houston, TX 77001
Mobil Jet Oil II
Mobil Oil Corp.
International Aviation Division
150n East 42nd Street
New York, NY 10017, USA
Mobil Oil Corp.
Aviation and Government Sales
3225 Gallows Road
Fairfax, VA 22037
Esso Petroleum Canada
55 St. Clair Avenue West
Toronto, Ontario
Canada M5W 2J8
Reissue 3
Original
8−23
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Royal Turbine Oil 500
Royal Lubricants Co. Inc.
P.O. Box 518
Hanover, NJ 07936
Turbonycoil 525-2A
Nyco S.A.
66Ave. Des Champs Elysee
Paris, France 75008
2. Main Transmission - Total Capacity 10.0 Quarts, 9.5 L
NOTE: Observe servicing instruction placard located on transmission oil filler.
Transmissions P/N 900D1400004-101 and 900D1400005-101:
MIL-PRF-23699
See item 1. Engine
Mobil Jet Oil 254
Transmission P/N 900D1400006-101:
Mobil AGL
NOTE: Do not use MobilSHC626lubricationoil designatedas
“NOTFORAVIATIONUSE"onthelabel. Refer to SB900-118.
3. Hydraulic System
MIL-PRF-83282
4. Rotor Brake
MIL-PRF-83282
Fuel system:
NOTE: The following fuel system servicing information pertains to both the standard
gravity filler port or the optional range extender filler port.
Fuel System Servicing Precautions
Only qualified authorized personnel may fuel the helicopter.
Static producing clothing shall not be worn.
Open flames and smoking are not permitted in refueling area.
Refueling vehicle should be parked a minimum of 20 feet from helicopter
during fueling operation.
At least one fully-charged 50 pound CO2 fire extinguisher shall be in the
immediate area.
Before starting fueling operation ground helicopter if possible.
Service fuel cell slowly.
Fuel system filling
NOTE: If the range extender is installed, the fuel quantity indication will not display actual
fuel weight when the fuel system is ‘‘topped off’’. The pilot must visually
determine fuel quantity by removing the fuel cap and noting fuel level on the
inside of filler neck (Ref. Figure 8−15).
Fuel helicopter with correct fuel as soon as possible after landing to prevent
moisture condensation.
8−24
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Keep fuel nozzle free of all foreign matter.
Always ground fueling nozzle or fuel truck to GROUND HERE receptacle
or to another bare metal location before removing service cap.
Remove the filler cap and secure the lanyard in the slot provided in the filler
cap adapter.
NOTE: The lanyard must be secured properly in order to assure that the gravity filler port
check valve fully opens.
CAUTION
Do not attempt to refuel helicopter if the lanyard has broken.
Service fuel cell slowly.
Secure filler cap after fueling.
Remove fuel nozzle and ground(s) from helicopter.
FUEL QUANTITY MARKS
146 - GAL
152 - GAL
156 - GAL
FUEL CAP LANYARD
FUEL SYSTEM RANGE EXTENDER
F90−097A
Figure 8−15. Fuel System Range Extender Gravity Filler Port
Reissue 3
Original
8−25
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Hydraulic System:
NOTE: The hydraulic system may be serviced by using either the optional hydraulic
system hand pump or a hydraulic mule. For servicing the system using the mule,
refer to the RMM, Section 12−00−00.
If the hand pump is not installed, the hydraulic fluid level must monitored closely
and serviced before leaving an area where proper facilities are located.
The hand pump (optional) provides capability to pump fluid into the manifold/res­
ervoir without the need of a ground support unit. The hand pump is mounted
next to the GSE panels on the transmission deck.
A sight glass indicates when the fluid is at the 0.3 qt level. On the underside
of the cover, a can opener provides a clean means of opening new cans of hydraulic
fluid.
A manually operated selector valve is mounted internally in the housing. The
selector valve lever provides for selection of system 1 or system 2 servicing.
The drive handle folds and clips against the reservoir housing for storage. When
in use, the handle extends through the open access panel, providing a convenient
means of operation.
NOTE: The following servicing procedure applies to aircraft equipped with the optional
hydraulic system hand pump.
CAUTION
Do not mix different specification hydraulic fluids. Ensure that only
MIL−PRF−83282 fluid is used to service the hydraulic systems for
all helicopter operations in temperatures above −40°F.
The intentional mixing of approved hydraulic oils is not permitted.
Servicing - Hydraulic hand pump:
Open transmission access panel (Ref. Figure 8-6 and Figure 8-7).
Verify that hydraulic fluid is low by checking oil level on hand pump reservoir
fluid level sight gauge (Ref. Figure 8-16).
Unscrew the reservoir cover to remove.
Add appropriate amount of hydraulic oil.
Replace cover.
Servicing - Hydraulic system:
Verify that pump reservoir has fluid; replenish if necessary.
Select system to be serviced by using the selector valve lever on the hand
pump (Ref. Figure 8-16).
Disengage handle from stowed position.
Rotate handle in direction of arrow (CW).
Servicing is complete when the hydraulic manifold fluid level sight gauge is
at the correct level.
Stow handle.
8−26
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
COVER
HANDLE (STOWED)
FLUID LEVEL
SIGHT GAUGE
MINIMUM OIL LEVEL
SELECTOR VALVE
LEVER
HANDLE IN
OPERATING POSITION
HAND PUMP (OPTIONAL)
FLUID LEVEL
SIGHT GAUGE
FILTER BYPASS
INDICATORS
FLUID TEMP
-40°C 95°C
F
F
U
U
L
L
L
L
R
E
R
F
E
I
F
L
I
L
L
L EMPTY
FLUID TEMP
-40°C
95°C
FULL
FULL
REFILL
REFILL
EMPTY
VIEW LOOKING DOWN
FILTER BOWL
(PRESSURE)
MANIFOLD / RESERVOIR
EARLY CONFIG
FILTER BOWL
(RETURN)
HYDRAULIC MAINFOLD
MANIFOLD / RESERVOIR
CURRENT CONFIG
F90−088A
Figure 8−16. Hydraulic System
Reissue 3
Original
8−27
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Main Transmission Filling
Open access panel (Ref. Figure 8-6 and Figure 8-7).
Open oil filler cap.
Pour in oil.
Verify quantity of oil in sight window.
NOTE: Correct oil livel is when the observed level is halfway between the “ADD” and
“FULL” marks (Ref. Figure 8−17).
Close oil filler cap.
Close access panel (Ref. Figure 8-6 and Figure 8-7).
Main Transmission Draining
Open access panel (Ref. Figure 8-6 and Figure 8-7).
Remove chip detector (Ref. RMM, Section 63-20-00).
Using transmission drain line, place free end of drain line in a suitable container.
Insert drain line probe in chip detector housing.
Allow transmission to drain.
Remove drain line and install chip detector (Ref. RMM, Section 63-20-00).
Close access panel (Ref. Figure 8-6 and Figure 8-7).
8−28
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
OIL FILLER
TRANSMISSION
OIL FILL
SERVICE WITH
MOBIL AGL OIL
CHIP
DETECTOR
HOUSING
NOTE: 900D1400006-101 TRANSMISSION ONLY
OIL LEVEL
INDICATOR
TRANSMISSION
OIL FILL
CHIP DETECTOR
SERVICE WITH OIL
PER MIL−L−23699
TRANSMISSION IS SERVICED
PROPERLY WHEN OIL LEVEL IS
HALFWAY BETWEEN “FULL” AND “ADD”.
NOTE: 900D1400004-101 AND 900D1400005-101
TRANSMISSIONS ONLY
FULL
FULL
ADD
ADD
VIEW ROTATED
FILTER IMPENDING BYPASS
INDICATOR
F90−075C
Figure 8−17. Main Transmission Servicing
Reissue 3
Revision 2
8−29
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Rotor brake:
The rotor brake reservoir is located on the top forward deck.
Open right-hand forward access door.
Remove filler cap.
Using hydraulic fluid, fill reservoir to top of sight glass.
Install filler cap.
Close right-hand forward access door.
FILLER CAP
SIGHT GLASS
F90−098
Figure 8−18. Rotor Brake
8−30
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Powerplant:
Engine Oil System Filling / Replenishing
Do not mix different brands or types of oil since their different
CAUTION chemical structures may make them incompatible. If different
brands or types of oil become mixed, drain system (including
engine integral oil tank, engine oil filter housing, engine oil heat
exchanger and oil in and out hoses) and refill with new oil.
NOTE: To reduce the possibility of over filling the oil tank, check the oil level 10 minutes
after engine shutdown.
Open oil dipstick hand hold/door (Ref. Figure 8-6 and Figure 8-7).
Remove engine oil filler cap.
Refill engine oil tank with specified oil in related manufacturers' publications
(Ref. RMM, Section 01-00-00)
NOTE: Correct oil level is when the observed level is between the MAX and MIN marks
on the oil dipstick. Filling the oil tank to MAX may result in oil being vented
overboard, causing a buildup of carbon deposits on the tailboom and
empennage. Should this occur, monitor engine oil level without adding oil (unless
the oil level falls below MIN) to determine if the level stabilizes at some point
between MAX and MIN. Once this level is determined, fill oil to and maintain this
level.
Replace oil filler cap.
Install and lock the oil filler cap on the oil transfer tube as follows (Ref.
Figure 8-19).
Make sure to install the oil filler cap correctly. Incorrect installation
can lead to disengagement of the cap locking lugs; the cap can
then lift from its locking position and have an incorrect sealing.
This can result in an oil loss that may require shuting down the
engine.
Place the dipstick in the gearbox and make sure that the dipstick off-set
of the cap is in line with the off-set hole of the oil filler tube of the gearbox.
Turn the handle and lock the cap. Make sure that the cap handle is in the
lock position.
If extra force is required to lock the cap, it means that the cap
CAUTION is not installed correctly. Remove the cap and reinstall it.
CAUTION
NOTE: The writing on the cap handle should be facing toward the front of the engine.
Close oil dipstick hand hold/door.
Draining fuel catch can (if installed)
NOTE: On a daily basis, drain the left and right hand fuel catch cans. Fuel draining from
overboard drain tube is an indication that fuel catch can is full and should be
drained immediately.
Place a suitable container below fuel catch can drain valve (Ref. Figure 8-14).
Push drain valve up and allow fuel to drain.
Reissue 3
Original
8−31
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
WRITING ON TAB FACING FORWARD
OIL LEVEL SIGHT
GLASS
OIL FILLER DIPSTICK
(VIEW ROTATED)
ENGINE OIL
FILTER CASE
OIL FILLER
DIPSTICK
OIL FILTER
IMPENDING
BYPASS INDICATOR
MINIMUM OIL LEVEL
CHIP
DETECTOR
OIL LEVEL SIGHT GLASS
OIL FILTER
IMPENDING
BYPASS INDICATOR
VIEW LOOKING AFT
NOTE: SOME DETAIL OMITTED FOR CLARITY
F90−076B
Figure 8−19. Engine Oil System − Servicing
8−32
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
8−6.
CSP−900RFM206A−1
Handling Servicing
and Maintenance
AIRCRAFT CLEANING
General cleaning of oil and dirt deposits from the helicopter and its components
can be accomplished by using dry-cleaning solvent, standard commercial grade
kerosene, or a solution of detergent soap and water. Exceptions that must be observed
are specified in the following cleaning paragraphs.
CAUTION
Storage, use, and disposal of all solvents must be per Government
and local health and safety regulations.
Fuselage Interior Trim and Upholstery:
Fuselage Interior Trim and Upholstery Cleaning
CAUTION
Carpet cleaning agents may damage underlying metal or composite
surfaces. Carpet or seats must be removed from helicopter prior
to cleaning and allowed to air dry prior to reinstallation.
Clean dirt or dust accumulations from floors and other metal surfaces with
vacuum cleaner or small hand brush.
CAUTION
Any flammable solvent that may affect material flammability must
be removed completely after cleaning.
Sponge soiled upholstery and trim panels with a mild soap and lukewarm
water solution. Avoid complete soaking of upholstery and trim panels. Wipe
solution residue from upholstery with cloth dampened by clean water.
CAUTION
Use solvents sparingly. Some solvents may soften or dull material.
Test an inconspicuous area prior to use.
Remove imbedded grease or dirt from upholstery and carpeting by sponging
or wiping with an upholstery cleaning solvent.
Helicopter Exterior:
Main Rotor Blade Cleaning
CAUTION
Use care to prevent scratching of fiberglass skin when cleaning
main rotor blades. Never use volatile solvents or abrasive materials.
Never apply bending loads to blades or blade tabs during cleaning.
NOTE: Avoid directing high pressure concentrations of soap and/or clean water toward
engine air intake areas, instrument static source ports and main rotor swashplate
bearings.
Clean rotor blades when necessary using solution of clean water and mild
soap.
Reissue 3
Original
8−33
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Fuselage Exterior Cleaning
NOTE: Avoid directing high pressure concentrations of soap and/or clean water toward
engine air intake areas, instrument static source ports and main rotor swashplate
bearings.
NOTE: Check and drain, if moisture present, the static system drain valves after the
aircraft has been washed or exposed to rain or snow and any time the airspeed
or altimeter indicators are showing sporadic readings. (Ref. Figure 8−6 and
Figure 8−7).
Clean helicopter exterior, including fiberglass/kevlar components, when nec­
essary, use solution of clean water and mild soap.
Transparent Plastic:
Transparent Plastic Cleaning
Clean outside surfaces of plastic panels by rinsing with clean water and rub­
bing lightly with palm of hand.
Use mild soap and water solution or aircraft type plastic cleaner to remove
oil spots and similar residue.
Never attempt to dry plastic panels with cloth. To do so causes
CAUTION any abrasive particles lying on plastic to scratch or dull surface.
Wiping with dry cloth also builds up an electrostatic charge that
attracts dust particles from air.
After dirt is removed from surface of plastic, rinse with clean water and let
air-dry.
Clean inside surfaces of plastic panels by using aircraft type plastic cleaner
and tissue quality paper wipers.
8−7.
COCKPIT DOOR REMOVAL
Cockpit Door Removal - early configuration (Ref. Figure 8-20):
Disengage gas strut from cockpit floor attachment.
NOTE: Fit between socket end of strut and ball end of ball stud is by interference.
Removal of strut from its attachment requires a snap action motion to pull away
the socket end from the ball stud.
Disengage door latching mechanism to open cockpit door assembly by pushing
on the door release handle.
Cockpit Door Removal - later configuration:
Disengage gas strut from cockpit floor attachment.
Remove lower quick release pin by pulling on the ring.
Remove door restraint by pulling away from lower fork assembly.
Remove upper quick release pin while holding the door.
Remove door.
Install quick release pins into upper and lower fork assemblies.
8−34
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Handling Servicing
and Maintenance
LATER CONFIGURATION
VIEW LOOKING OUTBOARD
LEFT SIDE SHOWN, RIGHT SIDE OPPOSITE
DOOR RELEASE HANDLE
DOOR
HANDLE
DOOR
RESTRAINT
EARLY CONFIGURATION
DOOR FRAME
RING
WINDOW FRAME
QUICK RELEASE PIN
LOWER FORK
ASSEMBLY
DOOR RESTRAINT
LOWER DOOR ATTACHMENT WITH
REMOVABLE RESTRAINT. UPPER
DOOR ATTACHMENT SIMILAR.
BALL SOCKET
GAS STRUT
BALL STUD
F90−092A
Figure 8−20. Cockpit Door Attachment
Reissue 3
Original
8−35
CSP−900RFM206A−1
Handling Servicing
and Maintenance
8−8.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CABIN SEATS: REMOVAL/INSTALLATION
Cabin Seat Removal:
First disengage upper quick disconnect fittings then lower quick disconnect fit­
tings from their anchor plates to release cabin seat assembly. Remove seat assem­
bly.
Cabin Seat Installation:
Align cabin seat assembly with floor anchor plates. First engage lower quick
disconnect fittings then upper quick disconnect fittings of cabin seat assembly
into mating roof and floor anchor plates to secure.
Ensure fittings are fully and properly engaged.
NOTE: PULLING/RELEASING THE KNURLED COLLAR ON
THE QUICK DISCONNECT RELEASES/ENGAGES
THE LOCKING MECHANISM
UPPER SEAT ATTACHMENT
QUICK DISCONNECT
ANCHOR PLATE
KNURLED COLLAR
LOWER SEAT ATTACHMENT
ANCHOR PLATE
F90−077
Figure 8−21. Cabin Passenger Seat Attachment
8−36
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
8−9.
CSP−900RFM206A−1
Handling Servicing
and Maintenance
COPILOT FLIGHT CONTROLS
PEDAL SHAFT
ASSEMBLY
PEDAL ADJUSTMENT PINS
PEDAL CRANK
ASSEMBLY
PEDAL DISENGAGE PIN
HOOK TAPE
F90−101A
Figure 8−22. Copilot Pedals
Copilot Pedals: Disengaging (Ref. Figure 8-22)
Copilots pedal shaft assemblies can be temporarily stowed in the full forward
position.
Pull up pedal adjustment pins.
Pull out pedal disengage pin.
Swing shaft assemblies forward to their hook tape secured positions.
Copilot Pedals: Engaging
Reengaging copilot's pedals is opposite of disengaging.
NOTE: Ensure that pedal adjustment pins are fully seated in pedal crank assemblies.
Reissue 3
Original
8−37
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
8−10. ENGINE CHARTS
The following charts define maintenance action requirements for engine over temper­
ature, overspeed, and overtorque.
AREA A - RECORD IN ENGINE LOG BOOK
(2.5 MINUTE RATING)
AREA B - RECORD IN ENGINE LOG BOOK
(CONTINUOUS OEI)
AREA C - RETURN ENGINE FOR OVERHAUL
980
940
EXHAUST GAS TEMPERATURE
925
920
902
900
880
863
860
ÉÉ
ÉÉ
ÉÉ
ÉÉ
ÉÉ
ÉÉ
ÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇ
AREA D
960
AREA D - DETERMINE CAUSE OF OVERTEMPERATURE
AND RECORD IN ENGINE LOGBOOK
AFTER 15 MINUTES OF CUMULATIVE OPERATION IN AREA `A',
OR 10 HOURS IN AREA `B', OR 5 EXCURSIONS IN AREA D ENGINE
MAINTENANCE IS REQUIRED
AREA C
AREA A
ÉÉÉÉÉ
ÉÉÉÉÉ
ÉÉÉÉÉ
ÉÉÉÉÉ
ÉÉÉÉÉ
AREA B
840
820
NO ACTION REQUIRED
800
0
5 20
30
60
1
90
120
2
150
180
3
210
240
4
TIME (MINUTES AND SECONDS)
270
300
5
330 SEC
MIN
Figure 8−23. EGT Vs Time − All Conditions Except Starting
8−38
Reissue 3
Original
F90−007
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
820
AREA A - VISUAL INSPECTION THROUGH EXHAUST DUCT AND
RECORD IN ENGINE LOG BOOK
AREA B - PERFORM HSI
AREA C - RETURN ENGINE TO OVERHAUL
AREA D - DETERMINE CAUSE FOR HUNG START AND CARRY
OUT DRY MOTORING RUN PRIOR TO ATTEMPTING
A RE-START
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇÇ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
AREA C
AREA B
760
650
AREA A
NO ACTION REQUIRED
AREA D
2
20
30
45
TIME (SECONDS)
F90−006
Figure 8−24. EGT Vs Time − Starting
112.4
POWER TURBINE SPEED (% RPM)
MEASURED GAS TEMPERATURE (EGT)
875
Handling Servicing
and Maintenance
AREA A - RETURN ENGINE TO OVERHAUL
104.5
100.0
NO ACTION REQUIRED
0
10
20
30
40
50
SEC
TIME (SECONDS)
F90−008A
Figure 8−25. Power Turbine (NP) Speed Vs Time
Reissue 3
Original
8−39
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
AREA A - RECORD IN ENGINE LOG BOOK (2.5 MINUTE RATING)
103
GAS GENERATOR SPEED − %N G
AREA B - RETURN ENGINE FOR OVERHAUL
AREA B
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
ÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉÉ
101
AREA A
98.7
NO ACTION REQUIRED
20
0
40
60
80
100
1
TIME (MINUTES AND SECONDS)
120
2
140
2.5
SEC
MIN
F90−009A
Figure 8−26. Compressor Turbine (NG) Speed Vs Time
TORQUE @100/104% NP
IIDS (XMSN)
ENGINE
AEO
OEI
AREA A
AREA B
AREA C
RECORD IN ENGINE LOGBOOK SEE NOTE 1 AND 2
RETURN ENGINE FOR OVERHAUL
RECORD IN ENGINE LOG BOOK (CONTINUOUS OEI)
133.3%
NOTE 1
OPERATION BETWEEN 124 - 130% TORQUE:
- RECORD AS 2.5 MINUTE RATING
- AFTER ONE HOUR OF CUMULATIVE RUNNING,
RETURN THE GEARBOX MODULE FOR OVERHAUL
OPERATION ABOVE 130% TORQUE - AFTER 5 EXCURSIONS, RETURN THE GEARBOX
MODULE FOR OVERHAUL
165%
NOTE 2
ÑÑ
ÑÑ
ÑÑ
ÑÑÑ ÑÑ
ÑÑÑ ÑÑ
ÑÑÑ ÑÑ
130%
104.5%
124%
100%
110%
2.5
MIN
ÇÇÇÇÇÇÇÇ
ÇÇÇÇÇÇÇÇ
AREA B
ÉÉÉÉ
ÉÉÉÉ
ÉÉÉÉ
AREA A
AREA C
88%
10
SEC
100%
MCP
NOTE:
MCP
THE TORQUE DISPLAYED ON
THE IIDS PRIMARY DISPLAY
IS TRANSMISSION TORQUE.
0
20
30
60
90 120 150 180 210
1
2
2.5
3
TIME (MINUTES AND SECONDS)
240
4
270
300
5
Figure 8−27. Engine Overtorque Limits − All Conditions
8−40
Reissue 3
Original
330
(SEC)
(MIN)
F90−132A
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
8−11. SPECIAL OPERATIONAL CHECKS AND PROCEDURES
The following checks are typically utilized as part of a post maintenance run up
associated with scheduled inspections, troubleshooting or maintenance on specific
aircraft systems. Refer to the Rotorcraft Maintenance Manual (CSP900RMM-2)
for the recommended use and frequency of the following checks.
CAUTION
These checks and or procedures are to be performed only while
aircraft is on the ground except where noted.
ENGINE NP OVERSPEED CHECK PROCEDURE
Left Engine
Engine control switches
IDLE
Right engine control switch
FLY (STABILIZE 100/104% NR)
OVSP TEST switch
MOVE TO THE LEFT AND HOLD
Left engine control switch
FLY
Left engine NP display
OBSERVE LEFT ENGINE Np INCREASE TO 85% −
95% (SLIGHT OSCILLATION MAY BE NOTICED) AND
LEFT EEC/MAN CAUTION LIGHTS ON.
OVSP TEST switch
RELEASE TO OFF POSITION
Left Engine NP display
OBSERVE LEFT ENGINE Np RESUMES NORMAL
GOVERNING AT 100/104%. LEFT EEC/MAN
CAUTION LIGHTS OUT.
Right Engine
Right engine control switch
IDLE
Left engine control switch
FLY − STABILIZE 100/104% NR)
OVSP TEST switch
MOVE TO THE RIGHT AND HOLD
Right engine control switch
FLY
Right engine NP display
OBSERVE RIGHT ENGINE Np INCREASE TO 85% −
95% (SLIGHT OSCILLATION MAY BE NOTICED) AND
RIGHT EEC/MAN CAUTION LIGHTS ON.
OVSP TEST switch
RELEASE TO OFF POSITION
Right engine NP display
OBSERVE RIGHT ENGINE NP RESUMES NORMAL
GOVERNING AT 100/104%. RIGHT EEC/MAN
CAUTION LIGHTS OUT.
Reissue 3
Revision 2
8−41
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
HYDRAULIC SYSTEM CHECK
With the aircraft operating at IDLE or FLY (100%):
IIDS secondary display
CHECK ‘‘1 HYD 2” CAUTION SEGMENTS ARE NOT
ILLUMINATED
With the aircraft operating at FLY (100%):
HYD TEST switch
SET AND HOLD TO ‘‘SYS 1”
IIDS secondary display
CHECK ‘‘1 HYD” CAUTION SEGMENT ILLUMINATES
IIDS alphanumeric display
VERIFY 250 PSI MAXIMUM FOR HYD 1 AND 1,000
HYD TEST switch
HYD TEST switch
IIDS secondary display
IIDS alphanumeric display
+100/−50 PSI FOR HYD 2
RELEASE AND CHECK ‘‘1 HYD” CAUTION
SEGMENT OFF
SET AND HOLD TO ‘‘SYS 2”
CHECK ‘‘HYD 2” CAUTION SEGMENT ILLUMINATES
VERIFY 250 PSI MAXIMUM FOR HYD 2 AND 1,000
+100/−50 PSI FOR HYD 1
Do not perform the following check if the helicopter is parked on
a wheeled platform, or slippery / icy surfaces. If unable to apply
right pedal or high resistance is felt, relax pressure on pedals and
release HYD TEST switch. Advise maintenance.
APPLY SUFFICIENT PRESSURE ON THE RIGHT
Anti-torque pedals
CAUTION
HYD TEST switch
PEDAL TO MOVE IT APPROXIMATELY 3 INCHES
(7.6 CM). REPEAT CHECK WITH LEFT PEDAL.
RELEASE AND CHECK ‘‘HYD 2” CAUTION
SEGMENT OFF
VSCS CHECK
NOTE: This functional check may be performed with the engines off and aircraft
connected to an external power source.
OFF
Left and right VSCS switches
IIDS alphanumeric display
VERIFY CAUTION SEGMENT ON AND ‘‘TOTAL STAB
FAIL” INDICATION
VSCS indicator needles
CENTERED
Left VSCS switch
ON
Right VSCS switch
MOMENTARILY TO ‘‘TEST” AND THEN TO ‘‘ON’’
IIDS alphanumeric display
VERIFY ‘‘RIGHT STAB FAIL” INDICATION FOR 5 TO 8
SECONDS, THEN OUT
Left VSCS switch
MOMENTARILY TO ‘‘TEST” AND THEN TO ‘‘ON’’
IIDS alphanumeric display
VERIFY ‘‘LEFT STAB FAIL” INDICATION FOR 5 TO 8
SECONDS, THEN OUT
VSCS indicator needles
VERIFY NEEDLES ARE APPROXIMATELY 55% RIGHT
OF CENTER WITH 0% CLP AND AIRCRAFT LEVEL
NOTE: If the selected VSCS system fails the test, the failure annunciation will remain
on the IIDS alphanumeric display.
8−42
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
WET ENGINE MOTORING RUN
CAUTION
Before performing this procedure, insure that the power supply
to the ignition exciter is disconnected (IGNTR circuit breakers
pulled).
CAUTION
When a fuel metering unit/pump is replaced in the field, motoring
or starting the engine is not recommended until priming is
accomplished by performing a engine wet motoring run.
Twistgrip on selected engine(s)
NORMAL
Fuel valve on
CHECK
Fuel boost pump
ON
Engine control switch
IDLE
NOTE: Maintain starter operation for desired duration while observing starter limits.
Engine control switch
OFF
Fuel boost pump
OFF
NOTE: After a wet motoring run, a dry motoring should be accomplished before any start
is attempted.
DRY ENGINE MOTORING RUN
NOTE: This procedure is used to clear internally trapped fuel and vapor from the engine.
This procedure maybe used if there is evidence of a fire within the engine or lack
of EGT indication after lightoff at the beginning of an engine start.
Twist grip
OFF
Engine control switch for selected engine
SET TO IDLE −
OBSERVE STARTER TIME LIMITS
Engine control switch for selected engine
OFF
EEC RESET button
PRESS
Twistgrip
PLACE IN NORMAL DETENT
EEC MAN or flashing indication
CHECK OFF
Reissue 3
Revision 2
8−43
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ENGINE OUT/LOW ROTOR WARNING CHECK
Engine control switches
FLY
Collective
INCREASE TO A CLP OF >5% FOR MORE
THAN 5 SECONDS
Collective
LOWER TO A CLP OF 0%
Engine control switches
SWITCH TO IDLE AND NOTE THE
FOLLOWING
ENG OUT warning light flashes and low rotor RPM tone is activated for one cycle. As
rotor RPM decreases through 88%, the low rotor RPM tone will reactivate until the
AOG logic disables the warning.
ENGINE WASH
Engine Water Wash - Desalination:
Open main transmission access door (Ref. Figure 8-6 and Figure 8-7).
NOTE: If cleaning agent is to be used, prepare solution and compressor wash system
in accordance with related manufacturers’ publications (Ref. RMM, Section
01−00−00)
CAUTION
Use of correct mixture as specified in the PWC Maintenance manual
is very important, not only when the temperature is below freezing
at the time of washing, but also if the temperature is expected to
be below 2°C (36°F) between time of washing and the next start.
Connect cleaning solution or water source to engine wash panel using AN type
fittings.
NOTE: To prevent precipitation of deposits through the use of hard water, engine must
be allowed to cool to below 65°C (150°F). Minimum cooling period of 40 minutes
must be allowed since the engine was last operated.
CAUTION
Ensure inlet particle separator and heat / defog shutoff valves are
turned off.
Do not motor engine for more than 30 seconds.
NOTE: Ensure cleaning solution or water source pressure of 60−82 PSI.
Perform dry engine motoring run; when NG reaches 5%, inject water solution
into air inlet case.
Close tank valve as soon as NG falls to 5%.
8−44
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CAUTION
CSP−900RFM206A−1
Handling Servicing
and Maintenance
Allow starter to cool between runs.
If water/methanol mixture has been used, perform additional dry engine motoring
run.
Close main transmission access door (Ref. RMM, Section 06-00-00).
Repeat procedure on other engine.
Once engine wash is complete, start and operate engines at idle for at least
one minute to completely dry engines.
Engine Wash - Performance Recovery:
Open main transmission access door (Ref. Figure 8-6 and Figure 8-7).
NOTE: If cleaning agent is to be used, prepare solution and compressor wash system
in accordance with related manufacturers’ publications (Ref. RMM, Section
01−00−00)
CAUTION
Use of correct mixture as specified in the PWC Maintenance manual
is very important, not only when the temperature is below freezing
at the time of washing, but also if the temperature is expected to
be below 2°C (36°F) between time of washing and the next start.
Connect cleaning solution or water source to engine wash panel using AN type
fittings.
NOTE: To prevent precipitation of deposits through the use of hard water, engine must
be allowed to cool to below 65°C (150°F). Minimum cooling period of 40 minutes
must be allowed since the engine was last operated.
CAUTION
Ensure inlet particle separator (IPS) and heat / defog shutoff valves
are turned off.
Do not motor engine for more than 30 seconds.
NOTE: Ensure cleaning solution or water source pressure of 60−82 PSI.
Perform dry engine motoring run (Ref. paragraph 8-11); when NG reaches 5%,
inject wash solution into air inlet case.
Close tank valve as soon as NG falls to 5%.
Allow cleaning solution to soak for 10 minutes.
Perform dry engine motoring run (Ref. paragraph 8-11); when NG reaches 5%,
inject one half of rinse solution into air inlet case.
Observe starter cooling period.
Perform dry engine motoring run (Ref. paragraph 8-11); when NG reaches 5%,
inject remainder of rinse solution into air inlet case.
Reissue 3
Original
8−45
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
If water/methanol mixture has been used, perform second dry engine motoring
run.
Close main transmission access door.
Repeat procedure on other engine.
Once engine wash is complete, start and operate engines at idle for at least
one minute to completely dry engines.
ENGINE WASH
NOZZLE
RIGHT ENGINE
WASH TUBE
ASSEMBLY
LEFT ENGINE WASH
TUBE ASSEMBLY
ENGINE
WASH
L
E
F
T
VIEW ROTATED
R
I
G
H
T
F90−066
Figure 8−28. Engine Wash Panel
8−46
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
MANUAL ENGINE SHUTDOWN CHECK
NOTE: This procedure should be performed with engine control switch in IDLE and all
unnecessary bleed air and electrical equipment, including generator, OFF.
Twist grip
IDLE DETENT
NP slows to idle
CHECK
EEC MAN indication on primary IIDS dis­
play
CHECK
Twistgrip
SNAP TO CUTOFF
Engine control switch
OFF
IIDS
CHECK NORMAL SHUTDOWN
INDICATIONS
NG zero percent
CHECK
EEC RESET button
PRESS
Twistgrip
PLACE IN NORMAL DETENT
CAUTION
DO NOT return twist grip to the NORMAL detent until NG is at zero
and the EEC RESET button is pressed. Failure to follow this
procedure may cause a re−light with a subsequent EGT
exceedance.
CHECK OFF
EEC MAN indication
Reissue 3
Original
8−47
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
MANUAL ENGINE START CHECK
NOTE: Complete the Engine Prestart cockpit check (Ref. Section IV) before attempting
a manual start.
Twistgrip
ROTATE TO FULL OPEN (PAST
THE ‘‘NORMAL’’ DETENT)
EEC MAN indication on primary IIDS dis­
play
CHECK
Twist grip
ROTATE TO OFF
Generator
OFF
L BOOST or R BOOST
ON, CHECK IIDS INDICATIONS
Engine control switch
IDLE
Twist grip
ROTATE TOWARD IDLE AS NG
INCREASES THROUGH 8
PERCENT
NOTE: As NG increases through 8% rotate twistgrip toward normal until lightoff occurs.
Observe EGT indication for immediate temperature rise. Monitor EGT and NG
during start. Observe start limits. Increase twistgrip toward normal only as
necessary to keep NG accelerating toward idle. Manually bring NP/NR to 65%.
CAUTION
If lightoff is not attained with an increase of EGT and NG within
10 seconds, rotate the twistgrip to OFF and place the engine control
switch to off. Following a 30 second fuel drain period, perform a
30 second dry motoring run before attempting another start. Repeat
the complete starting sequence observing limitations.
EEC RESET button
PRESS WHEN NP/NR IS 65
PERCENT
EEC MAN indication
CHECK FLASHING
Twistgrip
NORMAL DETENT
EEC MAN indication
CHECK OFF
Engine oil pressure
CHECK
Generator
ON
IIDS
CHECK
8−48
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Handling Servicing
and Maintenance
AUTOROTATION RPM CHECK
Refer to CSP-900RMM-2, Section 18-00-00.
NOTE: This procedure should be performed with engine control switches in FLY and
collective full down. However, aircraft operating at or near gross weight limits and
at high density altitudes may not be able to perform this procedure with collective
full down without exceeding rotor limits. Refer to CSP−900RMM−2, Section
18−00−00 for alternative collective position while operating at high gross
weights.
SELECT
Target altitude
NOTE: Select an altitude above target altitude so as to arrive at the target altitude in
steady state autorotation at 70 KIAS. Failure to maintain constant airspeed
during autorotation will cause rotor RPM fluctuations, resulting in inaccurate
RPM readings.
IIDS
SELECT “CLP” ON
ALPHANEUMERIC DISPLAY
Airspeed
70 KIAS
Collective lever position
ZERO % OR 10% AS REQUIRED
CAUTION
Observe rotor limits.
RECORD ROTOR RPM
At target altitude
NOTE: If gross weight/density altitude combination allows procedure with collective full
down, the torque reading should be zero percent at target altitude for accurate
autorotation RPM.
Reissue 3
Original
8−49
CSP−900RFM206A−1
Handling Servicing
and Maintenance
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
RESETTING IIDS TIME/DATE
TOP LEVEL
SECOND LEVEL
NOTE 1
SET TIME/DATE
TIME <HH:MM>
DATE MM-DD-YY
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
NOTE 1.: ``ENT'' KEY SELECTS FIELD TO BE SET (MINUTE,
HOURS, DAY, MONTH, YEAR) AND SELECTED FIELD
BLINKS, AND KEYS INCREMENT/DEINCRE­
MENT DIGIT VALUE, ``REC'' KEY CHANGES TIME
MENU
AND DATE TO SELECTED VALUES
F92−101
Figure 8−29. Set Time/Date
To change date or time:
This procedure is to be performed with both engines OFF.
Press MENU to enter menu system.
Use ↑ or ↓ keys to select SET TIME/DATE and press ENT. The following is
displayed on the IIDS two line alphanumeric display:
TIME HH:MM
DATE MM-DD-YY
Press ENT to edit display. The hour digits in the TIME HH:MM display will
blink indicating these are the digits selected for editing.
Use ↑ or ↓ keys to change value of flashing digit/value.
NOTE: Holding the arrow key for more than one second will cause the value of the
digit(s) being edited to increment at the rate of one per second.
Press ENT to select next digit(s) (the minutes digits will blink) and set value
using ↑ or ↓ keys.
NOTE: Each press of the ENT key will select the next value to edit in the sequence they
are displayed.
Repeat above steps until the correct time and date is displayed.
Use the REC key to save the changed time/date. Pressing the CLR key instead
of REC will abandon all changes.
NOTE: The REC key may be pressed at any time during the editing process to save the
changes made. Any fields not changed will remain at their present values.
8−50
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Additional Operations
and Performance Data
SECTION IX
ADDITIONAL OPERATIONS
AND PERFORMANCE DATA
TABLE OF CONTENTS
PARAGRAPH
PAGE
9-1. Abbreviated Checklists . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
9-1
9-2. Fuel Flow VS Airspeed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 9-1. Fuel Flow, Sea Level, ISA (15°C) . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 9-2. Fuel Flow, 4000 Feet HP, ISA (7°C) . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 9-3. Fuel Flow, 8000 Feet HP, ISA (-1°C) . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 9-4. Fuel Flow, Sea Level, ISA + 20°C (35°C) . . . . . . . . . . . . . . . . . . . . . .
Figure 9-5. Fuel Flow, 4000 Feet HP, ISA + 20°C (27°C) . . . . . . . . . . . . . . . . . . .
Figure 9-6. Fuel Flow, 8000 Feet HP, ISA + 20°C (19°C) . . . . . . . . . . . . . . . . . . .
Figure 9-7. Fuel Flow, Sea Level, ISA (15°C) - NACA Inlet . . . . . . . . . . . . . . . .
Figure 9-8. Fuel Flow, 4000 Feet HP, ISA (7°C) - NACA Inlet . . . . . . . . . . . . . .
Figure 9-9. Fuel Flow, 8000 Feet HP, ISA (-1°C) - NACA Inlet . . . . . . . . . . . .
Figure 9-10. Fuel Flow, Sea Level, ISA + 20°C (35°C) - NACA Inlet . . . . . . . .
Figure 9-11. Fuel Flow, 4000 Feet HP, ISA + 20°C (27°C) - NACA Inlet . . . . .
Figure 9-12. Fuel Flow, 8000 Feet HP, ISA + 20°C (19°C) - NACA Inlet . . . .
9-4
9-5
9-6
9-7
9-8
9-9
9-10
9-11
9-12
9-13
9-14
9-15
9-16
9-3. International Civil Aviation Organization (ICAO) Noise Levels . . . . . . . . . . . . . .
9-17
Reissue 3
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9−i
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
9−ii
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Additional Operations
and Performance Data
SECTION IX
ADDITIONAL OPERATIONS AND
PERFORMANCE DATA
9−1.
ABBREVIATED CHECKLISTS
NOTE: These checklists do not have any CAUTION, WARNINGS, or NOTES. Be sure
you have a thorough understanding of the checks as described in Section IV
before attempting to operate the helicopter.
ENGINE PRE−START COCKPIT CHECK
ELECTRICAL POWER − OFF
All cabin doors
CHECK
Seat belt and shoulder harness
FASTENED
Rotor brake
STOWED
Flight instruments
CHECK STATIC POSITION/SET
Collective friction
ON
Collective stick position
FULL DOWN
Twistgrip alignment marks aligned with in­
dex mark
CHECK
LDG/HVR lights
OFF
Key switch
ON
Circuit breakers
IN
Utility panel switches
OFF EXCEPT VSCS ON
Lighting control panel switches
AS REQUIRED
Avionics
AS DESIRED
L GEN and R GEN
ON (OFF FOR GPU START)
POWER
OFF
L BOOST AND R BOOST
OFF
CROSS FEED
OFF
LEFT/RIGHT FUEL SHUTOFF
ON; COVER CLOSED
L ENGINE and R ENGINE
OFF
Reissue 3
Original
9−1
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
ELECTRICAL POWER − ON
POWER
BAT/EXT
Monitor BIT
FIRE WARNING ANNUNCIATORS ON
FOR 2 SECONDS; CHECK IIDS FOR
ADVISORIES AT COMPLETION OF BIT
Fuel quantity display
CHECK
DISP (display by exception)
AS DESIRED
ENGINE STARTING − AUTOMATIC
L BOOST or R BOOST
ON; CHECK IIDS INDICATIONS
●
EEC MAN indicators
OFF
L ENGINE or R ENGINE
SET TO IDLE/FLY AS REQUIRED
IIDS
CHECK FOR NORMAL
INDICATIONS
Repeat starting procedure for second engine
GPU start only:
●
L GEN/R GEN
ON
●
GPU
DISCONNECT
ENGINE RUNUP
Avionics
ON, AS DESIRED
L ENGINE and R ENGINE
FLY
9−2
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Additional Operations
and Performance Data
BEFORE TAKEOFF
Cyclic control
CHECK RESPONSE
Collective friction
AS DESIRED
Primary and secondary IIDS displays
CHECK ADVISORIES
NP switch
HIGH
Utility panel switches
AS REQUIRED
ENGINE/AIRCRAFT SHUTDOWN − NORMAL
Collective stick
FULL DOWN/FRICTION ON
Cyclic stick
TRIM TO NEUTRAL
Pedals
NEUTRAL
L ENGINE and R ENGINE
IDLE
All unnecessary electrical equipment
OFF
Heat
OFF
AC (if installed)
OFF
Pitot heat (if installed)
OFF
IPS (if installed)
OFF
Lighting control panel
AS DESIRED
Avionocs master switch
OFF
L GEN/R GEN switches
OFF
L BOOST/R BOOST
OFF
L ENGINE and R ENGINE
OFF
ENG OUT indications
CHECK IIDS FOR NORMAL
INDICATIONS
Rotor brake (if installed)
APPLY BELOW
70% NR
IIDS
CHECK FOR INDICATIONS
OR MESSAGES
POWER
OFF
Reissue 3
Original
9−3
CSP−900RFM206A−1
Additional Operations
and Performance Data
9−2.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FUEL FLOW VS AIRSPEED
Description: The fuel flow charts presented in this section are based on level flight
performance data for helicopters equipped with the standard engine inlet (IPS or
screen) or the NACA inlet. Charts for the NACA inlet are labeled ``-NACA Inlet''.
Fuel consumption values are based on minimum specification engines and thus
may vary between engines. This data is based on a baseline aircraft with 15% electri­
cal load, engine bleeds and air conditioner off.
Use of Chart: Use the charts as illustrated by the example below.
NOTE: The following example uses Figure 9−1.
Example:
Wanted: Rate of fuel flow
Known: Airspeed = 115 KIAS
Known: Estimated gross weight = 5500 pounds
Method: Enter the chart at the known airspeed of 115 knots (interpolation re­
quired). Move vertically to the 5500 pound point (interpolation required)
then move to the left to the fuel flow scale and read a fuel flow of approxi­
mately 470 LB/HR.
9−4
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
MCP LIMIT
600
550
FUEL FLOW - LB/HR
500
450
6000 LB
LONG RANGE CRUISE
400
5000 LB
350
4000 LB
300
250
200
40
50
60
70
80
90
100
110
INDICATED AIRSPEED - KNOTS
120
130
140
150
F90−122
Figure 9−1. Fuel Flow, Sea Level, ISA (15°C)
Reissue 3
Original
9−5
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
MCP LIMIT
550
FUEL FLOW - LB/HR
500
450
6000 LB
400
350
LONG RANGE CRUISE
5000 LB
4000 LB
300
250
200
40
50
60
70
80
90
100
110
INDICATED AIRSPEED - KNOTS
120
Figure 9−2. Fuel Flow, 4000 Feet HP, ISA (7°C)
9−6
Reissue 3
Original
130
140
150
F90−123
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
600
550
MCP LIMIT
FUEL FLOW - LB/HR
500
450
400
6000 LB
LONG RANGE CRUISE
350
5000 LB
4000 LB
300
250
200
40
50
60
70
80
90
100
110
INDICATED AIRSPEED - KNOTS
120
130
140
150
F90−124
Figure 9−3. Fuel Flow, 8000 Feet HP, ISA (−1°C)
Reissue 3
Original
9−7
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
MCP LIMIT
550
FUEL FLOW - LB/HR
500
450
6000 LB
LONG RANGE CRUISE
400
5000 LB
350
4000 LB
300
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
Figure 9−4. Fuel Flow, Sea Level, ISA + 20°C (35°C)
9−8
Reissue 3
Original
140
150
F90−119
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
600
550
MCP LIMIT
FUEL FLOW - LB/HR
500
450
6000 LB
400
350
LONG RANGE CRUISE
5000 LB
300
4000 LB
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
140
150
F90−120
Figure 9−5. Fuel Flow, 4000 Feet HP, ISA + 20°C (27°C)
Reissue 3
Original
9−9
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
550
FUEL FLOW - LB/HR
500
MCP LIMIT
450
400
6000 LB
LONG RANGE CRUISE
350
5000 LB
300
4000 LB
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
Figure 9−6. Fuel Flow, 8000 Feet HP, ISA + 20°C (19°C)
9−10
Reissue 3
Original
140
150
F90−121
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
MCP LIMIT
600
550
6250 LB
FUEL FLOW - LB/HR
500
6000 LB
450
LONG RANGE CRUISE
400
4000 LB
350
5000 LB
300
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
140
150
F90-154-1
Figure 9−7. Fuel Flow, Sea Level, ISA (15°C) − NACA Inlet
Reissue 3
Original
9−11
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
MCP LIMIT
550
6250 LB
FUEL FLOW - LB/HR
500
6000 LB
450
400
LONG RANGE CRUISE
4000 LB
350
5000 LB
300
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
Figure 9−8. Fuel Flow, 4000 Feet HP, ISA (7°C) − NACA Inlet
9−12
Reissue 3
Original
140
150
F90-154-2
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
600
550
MCP LIMIT
FUEL FLOW - LB/HR
500
6250 LB
450
6000 LB
400
350
LONG RANGE CRUISE
4000 LB
300
5000 LB
250
200
40
50
60
70
80
90
100
110
120
130
140
150
INDICATED AIRSPEED - KNOTS
F90−154−3
Figure 9−9. Fuel Flow, 8000 Feet HP, ISA (−1°C) − NACA Inlet
Reissue 3
Original
9−13
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
MCP LIMIT
550
6250 LB
6000 LB
FUEL FLOW - LB/HR
500
450
LONG RANGE CRUISE
400
4000 LB
350
5000 LB
300
250
200
40
50
60
70
80
90
100
110
120
130
INDICATED AIRSPEED - KNOTS
Figure 9−10. Fuel Flow, Sea Level, ISA + 20°C (35°C) − NACA Inlet
9−14
Reissue 3
Original
140
150
F90−154−4
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Additional Operations
and Performance Data
700
650
600
550
MCP LIMIT
FUEL FLOW - LB/HR
500
6250 LB
450
6000 LB
400
LONG RANGE CRUISE
4000 LB
350
5000 LB
300
250
200
40
50
60
70
80
90
100
110
120
130
140
INDICATED AIRSPEED - KNOTS
150
F90−154−5
Figure 9−11. Fuel Flow, 4000 Feet HP, ISA + 20°C (27°C) − NACA Inlet
Reissue 3
Original
9−15
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
700
650
600
550
FUEL FLOW - LB/HR
500
MCP LIMIT
6250 LB
450
6000 LB
400
350
LONG RANGE CRUISE
4000 LB
300
5000 LB
250
200
40
50
60
70
80
90
100
110
120
130
140
INDICATED AIRSPEED - KNOTS
Figure 9−12. Fuel Flow, 8000 Feet HP, ISA + 20°C (19°C) − NACA Inlet
9−16
Reissue 3
Original
150
F90−154−6
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
9−3.
CSP−900RFM206A−1
Additional Operations
and Performance Data
INTERNATIONAL CIVIL AVIATION ORGANIZATION (ICAO) NOISE
LEVELS
The MD900 meets the ICAO Annex 16, Volume 1, Chapter 8 noise requirements
for level flight, takeoff/climb, and approach descent profiles at the certified maximum
gross weight of 6500 LB (2948.35 kg).
MD900
Configuration
Clean aircraft, doors on, no
external kits.
ENGINE: PW 206A
GROSS WEIGHT: 6500LB (2948.35 kg)
Level Flyover
EPNL
(EPNdB)
Takeoff
EPNL
(EPNdB)
Approach
EPNL
(EPNdB)
84.13
85.95
92.26
Reissue 3
Revision 2
9−17
CSP−900RFM206A−1
Additional Operations
and Performance Data
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
9−18
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
SECTION X
OPTIONAL EQUIPMENT
TABLE OF CONTENTS
PARAGRAPH
PAGE
10-1. General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-1
10-2. Listing - Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 10-1. Optional Equipment MD900 Helicopter . . . . . . . . . . . . . . . . . . . . . . .
10-3. Compatibility - Combined Optional Equipment . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 10-2. Optional Equipment Kit Compatibility - MD900 Helicopter . . . .
10-4. Optional Equipment Performance Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-1
10-2
10-2
10-2
10-3
10-5. Operating Instructions: Air Conditioning (P/N 900P7250302-101) . . . . . . . . . .
Figure 10-1. Air‐conditioning System Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-2. Air Conditioner Control . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-5
10-6
10-8
10-6. Operating Instructions: Controllable Landing/Search Light . . . . . . . . . . . . . . . . 10-9
Table 10-3. Landing, Hover and Search Light Switch Functions . . . . . . . . . . . 10-9
Figure 10-3. Collective Stick Switch Panel . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-10
Figure 10-4. Circuit Breakers - Console Mounted (Typical) . . . . . . . . . . . . . . . . 10-11
Figure 10-5. Circuit Breakers - Baggage Compartment Mounted (Typical) . . 10-12
10-7. Operating Instructions: Rotorcraft Cargo Hook Kit . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-6. VNE Placard . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-7. Weight and Balance Envelope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-8. Cargo Hook IIDS Menu . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-9. Cargo Hook Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-15
10-16
10-17
10-19
10-20
10-8. Operating Instructions: Windscreen Wipers . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-10. Windscreen Wiper with Optional Windscreen
Washer Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-11. Windscreen Wiper Control Switch . . . . . . . . . . . . . . . . . . . . . . . . . .
Servicing Materials - Windscreen Washer Fluid . . . . . . . . . . . . . . . . . . . . . . . . . .
10-9. Operating Instructions: Supplemental Fuel System . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-12. Switch and Indicator Light - Location Typical . . . . . . . . . . . . . .
Example I: Longitudinal CG Determination . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 10-4. Fuel Loading Table - Jet-A (6.8 LB/GAL) . . . . . . . . . . . . . . . . . . . . .
Table 10-5. Fuel Loading Table - Jet-B (6.5 LB/GAL) . . . . . . . . . . . . . . . . . . . . .
Figure 10-13. Fuel Station Diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-23
FAA Approved
Reissue 3
Revision 2
10-23
10-24
10-25
10-27
10-29
10-30
10-31
10-31
10-32
10−i
CSP−900RFM206A−1
Optional Equipment
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PARAGRAPH
PAGE
Figure 10-14. Supplemental Fuel System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-34
10-10. Operating Instructions: Rescue Hoist . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-15. Center of Gravity Envelope for Hoist Operations
Below 60 KIAS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-16. Rescue Hoist Controls . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
EXAMPLE I: Lateral CG Determination - Enroute (above 60 KIAS) . . . . . . . .
EXAMPLE II: Lateral CG Determination - Destination (below 60 KIAS) . . . .
EXAMPLE III: Lateral CG Determination - With Hoist Load . . . . . . . . . . . . . .
Figure 10-17. Allowable Rescue Hoist Loading Chart . . . . . . . . . . . . . . . . . . . . .
Figure 10-18. Rescue Hoist Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Table 10-6. Servicing Materials . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-11. Operating Information: -111/-117 IIDS Option . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-19. OEI Engine Torque Display . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
Figure 10-20. Single Engine Rate of Climb and Descent at VY, OEI MCP
6250 LBS Gross Weight . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
10-37
10-38
10-42
10-44
10-44
10-45
10-46
10-48
10-49
10-51
10-51
10-52
10-12. Operating Instructions: Fire Extinguishing System . . . . . . . . . . . . . . . . . . . 10-53
Figure 10-21. Fire Extinguishing System . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-55
10-13. Operating Instructions: Smoke Detector . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-57
Figure 10-22. Smoke Detector and Press-To-Test Switch Location. . . . . . . . . . 10-58
10−ii
FAA Approved
Reissue 3
Revision 2
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
SECTION X
OPTIONAL EQUIPMENT
10−1. GENERAL INFORMATION
This section provides general supplemental information on optional equipment for
the MD900 Explorer Helicopter. The information includes a listing of usable optional
equipment and compatibility of combined equipment on the helicopter.
Supplemental data is prepared and included in this section whenever the installation
of that equipment affects the FAA Approval Data for Limitations (Section II), Emer­
gency and Malfunction Procedures (Section III), Normal Procedures (Section IV),
and Performance Data (Section V).
The Flight Manual Supplemental Data is to be used in conjunction with the basic
Flight Manual data and takes precedence over that data when the equipment is
installed.
CAUTION
Be sure to include a review of the appropriate flight manual
supplemental data for type of optional equipment installed
(including STC items) as a regular part of preflight planning.
10−2. LISTING − OPTIONAL EQUIPMENT
Table 10-1 lists MDHI optional equipment items available that require supplemen­
tal data. Other optional equipment items may be found in the RMM.
SPECIAL NOTE:
Items in the table marked with an asterisk (*) are optional equipment items that
have had their supplemental data incorporated into the main body of the flight
manual and are identified by the statement, ``If installed''.
FAA Approved
Reissue 3
Original
10−1
CSP−900RFM206A−1
Optional Equipment
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Table 10−1. Optional Equipment MD900 Helicopter
Publication No.
Equipment
Air conditioner (P/N 900P7250302-101)
CSP-900RFM206A-1 - Section X
Search light
CSP-900RFM206A-1 - Section X
Cargo hook
CSP-900RFM206A-1 - Section X
Fire extinguishing system
CSP-900RFM206A-1 - Section X
Rescue Hoist
CSP-900RFM206A-1 - Section X
Windscreen Wipers
CSP-900RFM206A-1 - Section X
Supplemental Fuel System
CSP-900RFM206A-1 - Section X
-111 IIDS Option
CSP-900RFM206A-1 - Section X
* Dual pitot tube
CSP-900RFM206A-1
* Pitot heat
CSP-900RFM206A-1
* Rotor brake
CSP-900RFM206A-1
* Engine air particle separator filter
CSP-900RFM206A-1
* Indicates data incorporated into the flight manual (Sections I thru IX where
appropriate).
10−3. COMPATIBILITY − COMBINED OPTIONAL EQUIPMENT
Table 10−2. Optional Equipment Kit Compatibility − MD900 Helicopter
Compatibility: Blank = Yes; X = No
Optional Equipment
A.
B.
C.
D.
E.
A. Air conditioner
B. Search light
C. Engine air particle separator
D. Rotor brake
E. Dual pitot tube
F. Pitot heat
G. Cargo hook
H. Fire extinguishing system
I. Rescue Hoist
J. Windscreen Wipers
K. Supplemental Fuel System
L. -111 IIDS
10−2
FAA Approved
Reissue 3
Original
F.
G.
H.
I.
J.
K.
L.
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
10−4. OPTIONAL EQUIPMENT PERFORMANCE DATA
SPECIAL NOTE:
Optional equipment that affect IGE/OGE hover performance require
additional hover performance charts. All Optional Equipment hover
performance charts are located in Section V.
FAA Approved
Reissue 3
Original
10−3
CSP−900RFM206A−1
Optional Equipment
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−4
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Air−Conditioning System
10−5. OPERATING INSTRUCTIONS: AIR CONDITIONING (P/N 900P7250302−101)
PART I
GENERAL
The air-conditioning system circulates conditioned air throughout the cabin. A five
position rotary switch AC/VENT controls the vent fan and air-conditioning. COOL
HIGH provides air-conditioning at a high setting. COOL LOW provides air-condi­
tioning at a low setting, selected from the center console utility panel assembly.
The air-conditioning system provides ventilation, temperature, and humidity con­
trol. The air-conditioning system consists of:
Freon Compressor Assembly - Compresses the air conditioning system refriger­
ant.
Lines and Tubing - Routes refrigerant throughout the air conditioning system.
Condenser Fans - Induce ambient airflow over the condenser.
Condenser - Heat exchanger for the condensing refrigerant.
Receiver Dehydrator - Removes moisture from the air conditioning system refrig­
erant.
High Pressure Switch - Turns off the compressor in a high pressure condition
to prevent damage to air conditioning system.
Low Pressure Switch - Activates or deactivates the Freon compressor assembly
in a low pressure condition to prevent damage to the air conditioning system.
Thermal Expansion Valve - Regulates air conditioning system refrigerant injected
into the evaporator.
Evaporator - Heat exchanger that cools cabin air.
Evaporator Fan - Induces airflow through evaporator.
Three Way Valve Duct Assembly - Controls the flow of recirculated cabin air
or ambient air to the air conditioning system.
Three Way Valve Control Cable - Controls position of the three way valve.
The compressor is mounted on the gearcase of the right hand engine. The condenser
is placed under the floor of the baggage compartment with its associated heat transfer
equipment. Fan-driven cooling air for the condenser is taken in and discharged
through grilles in the belly just below the aft cabin door. The evaporator occupies
the forward end of the upper cowling. The air conditioning system makes use of
the ventilation system's ducting to direct the cooled air to cabin and cockpit, but
adds a manual valve to permit selection of fresh or recirculated air. The knob for
this push/pull control is on the rear cockpit wall above the pilot's right shoulder.
The other air conditioner controls are located on the Utility panel.
FAA Approved
Reissue 3
Original
10−5
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Air−Conditioning System
CABIN/PASSENGER COMPARTMENT
AIR OUT­
LETS
6 PLACES
HIGH PRESSURE
SWITCH
È
È
TXV
RECEIVER/
DRYER
EVAPORATOR
3 WAY
VALVE
WATER
SEPARATOR
RAM AIR IN
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÎÎÎ
ÏÏÏÏÏÏÏÏÏ
ÎÎÎ
ÏÏÏÏÏÏÏÏÏ
ÎÎÎ
ÏÏÏÏÏÏÏÏÏ
ÎÎÎ
ÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÎÎÎ
ÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏÏÏÏ
ÏÏÏÏÏÏÏÏÏ
CONDENSER
EVAP FAN
OVBD DRAIN
OVBD DRAIN
OVERBOARD
CONDENSER
FAN
COMPRESSOR
ASSEMBLY
LOW PRESSURE
SWITCH
CREW/PILOTS COMPARTMENT
AIR OUT­
LETS
4 PLACES
RECIRC
AIR INLET
FROM CABIN
ÈÈ
ÎÎ
ÈÈ
ÎÎÏ
Figure 10−1. Air-conditioning System Diagram
10−6
FAA Approved
Reissue 3
Original
HIGH PRESSURE LIQUID
LOW PRESSURE LIQUID
HIGH PRESSURE GAS
LOW PRESSURE GAS
9G21−020
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Air−Conditioning System
PART II
LIMITATIONS
No change.
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
As with any air conditioning system the installation in the MD900 has several built
in features to prevent damage. The compressor has an electrically controlled clutch
which is engaged when the system is turned on. Should the condenser fan fail
the high pressure gas coolant passing through the condenser will not become a liquid
due to heat retention. This will result in a higher than normal pressure in the lines
to the evaporator. When this condition is detected the clutch disengages the compres­
sor to prevent damage.
An automatic cutoff procedure similar to that for the heat/defog system shuts down
the air conditioner in flight if either engine becomes inoperative to maintain the
best power output from the running engine.
LOSS OF COOLING
Indications: No cooling air with system ON
Conditions: Automatic system safety shutdown, or internal failure
Procedures:
•
•
OFF
A/C control switch
Use fresh air vent system as required
FAA Approved
Reissue 3
Original
10−7
CSP−900RFM206A−1
Optional Equipment
Air−Conditioning System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART IV
NORMAL PROCEDURES
A five position rotary switch AC/VENT controls the vent fan and air-conditioning.
Selecting the COOL HIGH position provides air-conditioning at a high setting;
COOL LOW provides air-conditioning at a low setting, selected from the center
console utility panel assembly.
HYD
TEST
CAB
HEAT
SYS 1
OVRD
AC/VENT
ON
COOL
LOW
COOL
HIGH
OFF
VENT
LOW
VENT
HIGH
SYS 2
OFF
PITOT
HEAT
IPS
ON
ON
L VSCS R
ON
OFF
OFF
TEST
AC/VENT CONTROL
OFF
F90−056
Figure 10−2. Air Conditioner Control
PART V
PERFORMANCE DATA
Ref. Section V for hover performance with air‐conditioning on.
10−8
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Controllable Landing/Search Light
10−6. OPERATING INSTRUCTIONS: CONTROLLABLE LANDING/SEARCH
LIGHT
PART I
GENERAL
The controllable search light is located on the lower fuselage ahead of the forward
landing gear crosstube and offset to the left of the centerline.
In the stowed position, the search light is flush with the lower fuselage skin and
faces downward.
Illuminating the search light is accomplished through the hover and landing lights
switch while positioning the search light is accomplished by operating the five-posi­
tion search light switch (Ref. Figure 10-3).
PART II
LIMITATIONS
No Change.
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
No Change.
PART IV
NORMAL PROCEDURES
Table 10−3. Landing, Hover and Search Light Switch Functions
SWITCH
Hover and
Landing
Lights
Search Light
POSITION
FUNCTION
LDG
Switches landing, hover, and search light ON.
HVR
Switches hover and search light ON.
OFF
Turns hover, landing, and search lights OFF.
EXT
Press and hold switch to extend search light.
RET
Press and hold switch to retract search light.
L
Press and hold switch to rotate search light to the
left.
R
Press and hold switch to rotate search light to the
right.
FAA Approved
Reissue 3
Original
10−9
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Controllable Landing/Search Light
Preflight Checks - Electrical power OFF:
Search light
CHECK FOR BROKEN COVER,
DAMAGE TO MECHANICAL
ASSEMBLY OR BURNED OUT
BULB.
Console mounted LND LGT circuit breaker
IN (REF. FIGURE 10−4)
Baggage compartment mounted SRCH LT and
HOV SRCH LT circuit breakers
IN (REF. FIGURE 10−5)
Collective stick switch panel
CHECK FOR DAMAGE
LIGHTS switch and search light switch
(Ref. Figure 10-3)
HOVER AND LANDING LIGHT SWITCH
LIGHTS
SEARCH LIGHT SWITCH
LDG
EXT
HVR
L
OFF
R
GA
ÊÊÊ
ÊÊÊ
ÊÊÊ
ÊÊÊ
EEC
HIGH
NORM
UP
R
P
M
L
RESET
RET
R
COM
1
DOWN
2
1
COM
2
OFF
GATE
F90−116
Figure 10−3. Collective Stick Switch Panel
10−10
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Controllable Landing/Search Light
Preflight Checks - Electrical power ON:
NOTE: The following operational checks may be performed with an external power
source to prevent excessive battery drain.
Electrical master panel
BAT/EXT
POWER switch
Collective stick switch panel
LIGHTS switch to HVR (Ref. Figure 10-3)
CHECK HOVER AND SEARCH
LIGHTS ON
Use search light switch to rotate light left (L)
and right (R)
CHECK OPERATION
LIGHTS switch to LDG
CHECK HOVER, LANDING, AND
SEARCH LIGHTS ON
LIGHT switch to OFF
CHECK HOVER, LANDING, AND
SEARCH LIGHTS OFF
ESSENTIAL BUS
GCU
L
R
5
5
FUEL VLV
XFD
L
XMSN
FIRE
5
R
5
5
IIDS
FUEL
PROBE
LAND
LGT
5
10
VSCS
7
AUDIO
PNL 1
5
BLD AIR
LEAK
5
PITOT BLD AIR
TRIM HEAT 1 HEAT
5
7
5
ENG FIRE
L
R
5
5
INST STBY
FLOOD ATT
5
NAV XPNDR DIR
COM 1
1
GYRO 1
7
F90−118
Figure 10−4. Circuit Breakers − Console Mounted (Typical)
FAA Approved
Reissue 3
Original
10−11
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Controllable Landing/Search Light
LEFT GENERATOR BUS
AUDIO
PNL2
CRGO
HOOK
EVAP
VENT
EVAP
BATTERY BUS
CKPT
UTIL
CAB
UTIL
L
COMP
PITOT
HEAT2
L
CNDSR
FAN 2
CNSL
ATT
GYRO2
R
R
DETENT
LIGHT
MSTR
RIGHT GENERATOR BUS
L
BST PMP
INSTR
AV
MSTR
EEC
R
FUEL
LOW
OFF
GATE
L
POSN
STROBE
RTR
BRK
FIRE
HRD
LIGHTING
IGNTR
R
AREA
20
IIDS
TRAK
STB
CFU
AV
FAN
IPS
ATT
GYRO1
LAND
LGT
CNDSR
FAN 1
ENC
ALT
SRCH LT
L FLD
EXCIT
RT FLD
EXCIT
LEFT AVIONICS BUS
HOV
SRCH LT
RIGHT AVIONICS BUS
ADF2
RADAR
RT
RADAR
IND
RADAR
INVTR
RAD
ALT
ADF1
FM
CTRL
FM1
RT
MKR
BCN
COM2
XPNDR
2
DIR
GYRO2
NAV 2
DME
LORAN
GPS
FM2
RT
FM3
RT
F90−117
Figure 10−5. Circuit Breakers − Baggage Compartment Mounted (Typical)
10−12
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Controllable Landing/Search Light
PART V
PERFORMANCE DATA
No change.
PART VI
WEIGHT AND BALANCE DATA
No change.
PART VII
SYSTEM DESCRIPTION
The search light is controlled by the three position LIGHTS toggle switch. This
switch connects battery bus power to the search light through the hover and landing
light relays.
Movement of the search light is accomplished by actuating the search light switch
located on the collective stick switch panel.
Maximum light extension is 120° from stowed.
If the search light is rotated 90° either side of center and with an extended segment
of 0° to 60°, an interlock switch automatically deenergizes the lamp while positioning
the light is still possible.
PART VIII
HANDLING SERVICING AND MAINTENANCE
No change.
PART IX
ADDITIONAL OPERATIONS AND PERFORMANCE DATA
No change.
FAA Approved
Reissue 3
Original
10−13
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Controllable Landing/Search Light
This page intentionally left blank!
10−14
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
10−7. OPERATING INSTRUCTIONS: ROTORCRAFT CARGO HOOK KIT
PART I
GENERAL
The cargo hook is an option that permits the helicopter to carry a jettisonable external
load of up to 3,000 pounds. The hook is suspended by a bridle of four cables that
attach to the landing gear saddle fittings, and join at the cargo load cell link to
support the hook.
The pilot's controls for the hook consist of an electric release push-button on the
top of the cyclic grip and a manual/emergency cargo hook release mechanism.
Quick disconnect pins at the four attachment points for the bridle allow the flight
crew to install or remove the hook assembly. Quick disconnects for the electric and
mechanical release cables are located on the bottom of the fuselage near the forward
cross tube.
When the kit is installed, an owner or operator holding a valid Rotorcraft External
Load Operator Certificate may utilize the helicopter for transportation of external
cargo when operated by a qualified pilot. OPERATIONS WITH CARGO ON THE
HOOK SHALL BE CONDUCTED IN ACCORDANCE WITH APPLICABLE POR­
TIONS OF FEDERAL AVIATION REGULATIONS PART 133.
Information provided in this supplement is presented with the intent of furnishing
important data that can be used in the Rotorcraft Load Combination Flight Manual.
The Combination Flight Manual, which is required by FAR Part 133, will be prepared
by the applicant to obtain the rotorcraft External Load Operator Certificate.
FAA Approved
Reissue 3
Original
10−15
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART II
LIMITATIONS
Weight Limitations:
Maximum weight allowed on the landing gear is 6500 pounds.
Weight in excess of 6500 pounds and up to 6900 pounds must
be external and jettisonable.
CAUTION
Maximum Rotorcraft - Load Combination operating gross weight is 6900 pounds.
Center of Gravity Limitations:
See Figure 10-7.
Cargo Hook Limitations:
Maximum weight on the hook is 3000 LBS unless placarded otherwise (Ref.
Figure 10-9).
Airspeed Limitations:
With no load on hook, maximum VNE is 90 KIAS.
With load on hook, maximum VNE is 100 KIAS (Ref. Figure 10-6).
NOTE: Use caution as size and shape of load, and load attaching cable size and length
may affect flight characteristics. Satisfactory flight characteristics have been
demonstrated with a compact load.
Placards: Placard located on instrument panel.
20000
DENSITY ALTITUDE - FEET
15000
VNE WITH LOAD ON THE HOOK
10000
5000
VNE WITH NO LOAD ON
THE HOOK IS 90 KIAS
0
40
50
60
70
80
90
INDICATED AIRSPEED - KNOTS
Figure 10−6. VNE Placard
10−16
FAA Approved
Reissue 3
Original
100
110
F90−019−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
7000
6500
LONGITUDINAL CG
ENVELOPE
WEIGHT - POUNDS
6000
5500
5000
NORMAL CG LIMITS
4500
CARGO HOOK
CG LIMITS >6500 lbs
4000
3500
3000
194
198
196
200
202
FUSELAGE STATION (IN.)
208
206
204
7000
6500
LATERAL CG
ENVELOPE
WEIGHT - POUNDS
6000
5500
NORMAL CG LIMITS
5000
CARGO HOOK
CG LIMITS >6500 lbs
4500
4000
3500
3000
−5
−4
−3
−2
−1
0
1
LATERAL CG STATION (IN)
2
3
4
5
Figure 10−7. Weight and Balance Envelope
FAA Approved
Reissue 3
Original
F90−055A
10−17
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
The presence of an external load may further complicate procedures following an
emergency or malfunction. Release of loads attached through the cargo hook should
be considered consistent with safety of flight factors.
Emergency Release:
Actuate the mechanical release handle, mounted on the cyclic stick, to release
cargo in the event of an electrical failure.
PART IV
NORMAL PROCEDURES
Preflight Checks (Ref. Figure 10-9):
Verify security of cargo hook bridle attach points.
Visually inspect hardware for damage or indications of possible fatigue.
Check for fraying, wear or any other form of damage to the cable bridle assembly.
Inspect electrical release, and load indicating wire harness and connectors for gener­
al condition and security.
Examine manual release cable housing for nicks, cuts, kinks or general damage
that might restrict movement of cable within housing.
Inspect manual release connector for general condition and security.
Ensure a service loop is present in the manual release cable at cargo hook.
Inspect hook for general condition.
Cargo Hook Operational Checks:
NOTE: Functional checks of the cargo hook require an external power source for
electrical power or an operating engine.
Ensure that the CRGO HOOK circuit breaker (left generator bus) is IN.
NOTE: Refer to Chapter 25−55−00 in the RMM for special functional checks required
following the initial installation of the cargo hook kit or following replacement of
the manual release cable.
10−18
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
With the load beam in its locked position, apply pressure to simulate a load on
the beam and functionally check the three methods of cargo hook release:
Mechanical release lever on the right side of hook
Manual cargo hook release handle on cyclic
Electric cargo hook release switch on cyclic
NOTE: The TARE weight should be reset each time following aircraft shutdown and
restart.
Operating Procedures:
CAUTION
Use care to avoid passing load attaching cables over landing gear
skid tube when attaching load to hook with helicopter on the
ground.
Apply collective smoothly when lifting cargo.
With the hook weight suspended, and the selection made on the IIDS panel
menu for HOOK WT (Ref. Figure 10−8), the load indication should read HOOK
WT. xxxx LBS on the alphanumeric display.
Ensure that there is adequate clearance between the sling load and any obstacles
along the takeoff flightpath.
Activate cargo release switch on cyclic stick to release cargo.
Check CARGO HOOK OPEN advisory on IIDS alphanumeric display.
NOTE: Ground support personnel should manually assure positive reset of the cargo
hook after use of mechanical release, prior to further cargo pickups.
Instruct ground crew to ensure that the helicopter has been electrically grounded
prior to attaching cargo to drain charges of static electricity that may build up
in flight.
CAUTION
TOP LEVEL
HOOK WT 2456 LBS
The cargo hook extends 18 inches below the landing gear while
hovering. Ensure that there is adequate clearance between the
cargo hook and any obstacles along the flightpath.
SECOND LEVEL
ZERO WEIGHT DISP
2456 LBS
PRESSING “ENT” FOR MORE THAN 2 SECONDS
TAKES A TARE READING AND ZEROS DISPLAY
“ENT” SELECTS DIGITS TO BE EDITED (LEFT TO RIGHT),
SET CALIB CODE
<XXXX>
AND KEYS INCREMENT/DEINCREMENT DIGIT VALUE,
“REC” KEY CHANGES CODE TO SELECTED VALUE,
NOTE: TO RETURN TO PREVIOUS HIGHER LEVEL - PRESS
MENU
Figure 10−8. Cargo Hook IIDS Menu
FAA Approved
Reissue 3
Original
F90−153
10−19
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
QUICK RELEASE PIN
(SEE NOTE)
LINK ASSEMBLY
AFT SADDLE CLAMP
CABLE
QUICK
RELEASE PIN
(SEE NOTE)
PIN LINK
FORWARD
PIN LINK
LINK ASSEMBLY
FWD SADDLE CLAMP
CABLE
NOTE: ENSURE QUICK RELEASE
PIN HEAD FACES ``UP''
AFTER INSTALLATION
LH AFT LANDING
GEAR FITTING
MAX WORKING
LOAD 2200 LB
RH AFT LANDING
GEAR FITTING
CARGO HOOK PLACARD
LH FWD LANDING
GEAR FITTING
RH FWD LANDING
GEAR FITTING
CYCLIC STICK
SERVICE LOOP
CARGO HOOK
MECHANICAL
RELEASE LEVER
LOAD BEAM
LOAD INDICATOR
ELECTRICAL CONNECTOR
MANUAL CARGO HOOK
RELEASE
ELECTRICAL RELEASE
CONNECTOR
MANUAL RELEASE
CABLE CONNECTION
ELECTRIC CARGO
HOOK RELEASE
CYCLIC GRIP ROTATED
F90−057A
Figure 10−9. Cargo Hook Installation
10−20
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
PART V
PERFORMANCE DATA
Hover Ceiling:
Use the OGE hover ceiling charts: Refer to Section V for Hover Ceiling Data.
PART VI
WEIGHT AND BALANCE DATA
Cargo Hook Longitudinal CG: 203.0 In.
Cargo Hook Assembly Weight: 26.12 lbs.
The following table of Cargo Hook Loads may be used by the operator to assist
in determining the helicopter center of gravity.
Cargo Weight
(lb)
Moment/100
(in.−lb)
Cargo Weight
(lb)
Moment/100
(in.−lb)
100
20300
1600
324800
200
40600
1700
345100
300
60900
1800
365400
400
81200
1900
385700
500
101500
2000
406000
600
121800
2100
426300
700
142100
2200
446600
800
162400
2300
466900
900
182700
2400
487200
1000
203000
2500
507500
1100
223300
2600
527800
1200
243600
2700
548100
1300
263900
2800
568400
1400
284200
2900
588700
1500
304500
3000
609000
FAA Approved
Reissue 3
Original
10−21
CSP−900RFM206A−1
Optional Equipment
Rotorcraft Cargo Hook Kit
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART VII
SYSTEM DESCRIPTION
Cargo Hook Installation (Figure 10-9):
Align cargo hook cable attaching hardware with landing gear saddle clamp assem­
blies.
Install FWD link assemblies into FWD saddle clamps.
Install FWD pin links into link assemblies and quick release pins into FWD
pin links.
Connect cargo hook electrical connector, load indicator electrical connector and
mechanical release control cable connector.
Repeat procedure for aft link assembly attachment.
Perform cargo hook preflight and operational checks.
Cargo Hook Removal (Figure 10-9):
Remove quick release pins from Aft pin links and remove cable assembly from
aft saddle clamps.
Disconnect cargo hook electrical connector, load indicator electrical connector
and manual release control cable connector.
Remove pin links attaching cargo hook cables and cargo hook to FWD landing
gear saddle clamp assemblies.
Remove cargo hook and bridle assembly.
10−22
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Windscreen Wipers
10−8. OPERATING INSTRUCTIONS: WINDSCREEN WIPERS
PART I
GENERAL
The windscreen wipers provide the pilot a means to clear the windscreens of rain
or snow.
The windscreen washers (if installed) provide pressurized washer fluid to the wind­
screen through spray nozzles. The washer pump and reservoir are located in the
battery compartment.
There are no changes to limitations, emergency procedures, or performance data
with the installation of the windscreen wipers or windscreen washers.
WINDSCREEN
WIPERS
WASHER
RESERVOIR
WASHER PUMP
F90-159A
Figure 10−10. Windscreen Wiper with Optional Windscreen Washer Installation
FAA Approved
Reissue 3
Original
10−23
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Windscreen Wipers
PART IV
NORMAL PROCEDURES
Windscreen wipers:
Use the windscreen wipers whenever it is necessary to clear the windscreens
of rain or snow.
Do not use the windscreen wipers on a dry windscreen.
The wipers have a panel mounted control switch (Ref. Figure 10-11). The switch
has four positions:
PARK, OFF, LOW, and HIGH.
The PARK position is a momentary position and is used to stow the wipers when
not in use.
The OFF position turns the wipers off.
The LOW and HIGH positions refer to wiper speed. Select the speed appropriate
for weather conditions.
The three position toggle switch HIGH (HI) and LOW (LO) positions function
as above. The OFF position parks and turns the wipers off.
Windscreen washer (if installed):
Preflight Check
Check washer reservoir fluid level.
On dry windscreen
Press and hold the WASHER button for two to three seconds before turning
the WINDSHIELD WIPERS switch to LOW. Turn off wipers while windscreen
is still wet.
During wiper operation
Press and hold the WASHER button for two to three seconds or as needed
to clear the windscreen.
Cold weather operation
Use 50 percent by volume isopropyl alcohol mixed with distilled or deionized
water when temperatures are at or below 0°C.
WASHER CONTROL SWITCH
(IF INSTALLED)
ROTARY CONTROL SWITCH
3-POSITION TOGGLE SWITCH
WINDSHIELD
WIPERS
OFF
PARK
LOW
3-POSITION LOCKING
TOGGLE SWITCH
WINDSHIELD
WIPERS
HIGH
HIGH
WIPERS
HI
LO
LOW
WASHER
OFF
OFF
DO NOT OPERATE WIPERS
ON DRY WINDSCREEN
DO NOT OPERATE WIPERS
ON DRY WINDSCREEN
DO NOT OPERATE WIPERS
ON DRY WINDSCREEN
Figure 10−11. Windscreen Wiper Control Switch
10−24
FAA Approved
Reissue 3
Original
F90-160B
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Windscreen Wipers
PART VI
WEIGHT AND BALANCE DATA
ITEM
WEIGHT
(LB)
STATION
(ARM)
MOMENT
(IN−LB)
Washer reservoir full - water only
Washer reservoir full - water alcohol mixture
4.8
4.3
82.7
82.7
394
356
PART VIII
HANDLING, SERVICING AND MAINTENANCE
Servicing Materials − Windscreen Washer Fluid
Specification
Material
Manufacturer
Washer reservoir - Total Capacity approximately 2 US quarts.
None
Distilled or deionized water for opera­
tions above freezing and 50 percent by
volume mixture of isopropyl alcohol
and distilled or deionized water for op­
erations below freezing.
FAA Approved
Reissue 3
Original
None
10−25
CSP−900RFM206A−1
Optional Equipment
Windscreen Wipers
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−26
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
10−9. OPERATING INSTRUCTIONS: SUPPLEMENTAL FUEL SYSTEM
PART I
GENERAL
The MD900 supplemental fuel system option adds a transfer type auxiliary fuel
tank located below the baggage compartment floor. Refer to Part VII for system
description.
PART II
LIMITATIONS
Placards:
SUPPLEMENTAL FUEL SYSTEM
USE MAIN FUEL DOWN TO
700 LBS BEFORE SELECTING
AUX FUEL TRANSFER
LOCATED BY AUXILIARY FUEL GAUGE.
NOTE: LOCATION MAY VARY.
LOCATED ABOVE FUEL FILLER
F90-157B
FAA Approved
Reissue 3
Revision 2
10−27
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART IV
NORMAL PROCEDURES
Preflight checks:
Prestart cockpit check:
Inflight operation:
SECURED
Fuel cap
OFF
Fuel transfer switch
ON; VERIFY FUEL TRANSFER LIGHT
‘‘ON’’
Fuel transfer switch
NOTE: Fuel transfer should be begun when the fuel level in the main tank is between
700 and 300 LBS.
Main fuel tank quantity begins to
increase and auxiliary fuel quantity
begins to decrease.
CHECK
NOTE: Fuel Transfer:
Fuel transfer time is approximately 20 minutes (22 minutes if second check valve
installed) with a full auxiliary fuel tank while in normal cruise. Transferring fuel
to the main tank may be accomplished once main tank indicated fuel quantity
is at or less than approximately 500 LB in normal ground attitude or
approximately 700 LB in normal cruise attitude.
Fuel transfer rate is approximately 600 LB/HR (540 LB/HR with second check
valve) in normal cruise and approximately 400 LB/HR in normal ground attitude.
CAUTION
Starting Fuel Transfer below 300 LBS:
With engines at MCP, the auxiliary fuel transfer rate may not keep
up with the engine fuel consumption rate. This does not pose a
problem as long as fuel transfer is begun before main fuel is below
300 LBS.
OFF WHEN TRANSFER IS COMPLETE
Fuel transfer switch
NOTE: The auxiliary fuel quantity gauge has been found to be inaccurate (indicates
high) during hover operations.
Engine/aircraft shutdown
10−28
Fuel transfer switch
OFF; VERIFY FUEL TRANSFER LIGHT
‘‘OFF’’
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
SUPPLEMENTAL FUEL SYSTEM
USE MAIN FUEL DOWN TO
700 LBS BEFORE SELECTING
AUX FUEL TRANSFER.
ON
FUEL TRANSFER SWITCH
FUEL TRANSFER INDICATOR LIGHT
OFF
E
50 100 150
F
AUXILIARY FUEL QUANTITY GAUGE
AUX FUEL
GAUGE, SWITCH AND INDICATOR LIGHT
F90-155A
Figure 10−12. Switch and Indicator Light − Location Typical
FAA Approved
Reissue 3
Original
10−29
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART VI
WEIGHT AND BALANCE DATA
Weight and balance characteristics:
The lateral CG of the auxiliary fuel tank is at station -2.0.
Calculate CG as shown in the example below.
Example I: Longitudinal CG Determination
ITEM
Basic Weight
WEIGHT
(LB)
STATION
(ARM)
3512.4
MOMENT
(IN−LB)
738045
Pilot
185.0
130.70
24180
Copilot/Passenger
185.0
130.70
24180
Passenger - Rear Facing R/H
175.0
173.0
30275
Passenger - Rear Facing L/H
175.0
173.0
30275
Passenger - FWD Facing R/H
175.0
213.0
30275
Passenger - FWD Facing L/H
175.0
213.0
30275
1. Zero Fuel Weight
4582.4
201.1
30275
2. Add: Fuel - Main Tank Only (Jet-A)
Gross Weight:
1025.0
5607.4
191.2
199.3
195980
1117484
3. Add: Fuel - Auxiliary Tank Only
Gross Weight:
200.0
4782.4
244.8
202.9
48960
970464
4. Add: Fuel - Both Tanks
Gross Weight:
1225.0
5807.4
200.9
1166444
10−30
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
Table 10−4. Fuel Loading Table − Jet−A (6.8 LB/GAL)
FUEL WEIGHT
(LB)
LONGITUDINAL LONGITUDINAL
STATION
MOMENT
LATERAL
STATION
LATERAL
MOMENT
20
239.4
4789
-2.0
-40
40
240.6
9625
-2.0
-80
60
241.6
14494
-2.0
-120
80
242.3
19387
-2.0
-140
100
242.9
24294
-2.0
-200
120
243.4
29210
-2.0
-240
140
243.8
34133
-2.0
-280
160
244.1
39062
-2.0
-320
180
244.4
44000
-2.0
-360
200
244.8
48951
-2.0
-400
Table 10−5. Fuel Loading Table − Jet−B (6.5 LB/GAL)
FUEL WEIGHT
(LB)
LONGITUDINAL LONGITUDINAL
STATION
MOMENT
LATERAL
STATION
LATERAL
MOMENT
20
239.5
4790
-2.0
-40
40
240.7
9629
-2.0
-80
60
241.7
14501
-2.0
-120
80
242.5
19397
-2.0
-140
100
243.1
24306
-2.0
-200
120
243.5
29224
-2.0
-240
140
243.9
34149
-2.0
-280
160
244.3
39080
-2.0
-320
180
244.6
44022
-2.0
-360
200
244.9
48982
-2.0
-400
FAA Approved
Reissue 3
Original
10−31
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
FUEL WEIGHT − LB
JET − A (6.8 LB/GAL)
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
238.0 238.5 239.0 239.5 240.0 240.5 241.0 241.5 242.0 242.5 243.0 243.5 244.0 244.5 245.0
FUSELAGE STATION − INCHES
FUEL WEIGHT − LB
JET − B (6.5 LB/GAL)
210
200
190
180
170
160
150
140
130
120
110
100
90
80
70
60
50
40
30
20
10
0
238.0 238.5 239.0 239.5 240.0 240.5 241.0 241.5 242.0 242.5 243.0 243.5 244.0 244.5 245.0
FUSELAGE STATION − INCHES
F90-156
Figure 10−13. Fuel Station Diagram
10−32
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
PART VII
SYSTEM DESCRIPTION
The MD900 supplemental fuel system option adds a transfer type auxiliary fuel
tank with a usable capacity of approximately 29.4 US gallons (200 LB, Jet-A) under­
neath the baggage compartment floor. The tank is filled through a gravity fill port
on the right side of the aircraft. Transfer into the main tank is performed using
a fuel transfer pump mounted in the auxiliary fuel tank. Overfilling the main tank
is prevented by use of a float-type level control valve mounted in the main tank.
This level control valve prevents transfer into the main tank until the fuel remaining
in the main tank is less than approximately 500 LB in normal ground attitude
or approximately 700 LB in normal cruise attitude. The level control valve will
shut off transfer into the main tank if the fuel in the main tank increases to approxi­
mately 755 LB in normal ground attitude or approximately 832 LB in normal cruise
attitude. An inline check valve is installed in the fuel transfer line in the main
fuel tank to prevent backflow of fuel from the main tank into the auxiliary tank.
A second check valve may be installed in the auxiliary fuel tank transfer line that
prevents gravity transfer from the auxiliary tank into the main tank in high-speed
cruise flight. The auxiliary tank vent is teed into the existing main tank aft vent
tubing.
The installation includes a cockpit mounted fuel quantity gauge (AUX FUEL) for
the auxiliary tank, a fuel transfer pump switch, and a fuel transfer indicator light.
Electrical power is supplied from the battery bus through the ``AUX FUEL'' 5 AMP
circuit breaker. A separate 1 AMP ``AUX FUEL XMIT'' circuit breaker provides
power for fuel quantity indicating. These circuit breakers are located on the baggage
compartment circuit breaker panel under ``BATTERY BUS''.
FAA Approved
Reissue 3
Original
10−33
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Supplemental Fuel System
FUEL VENT ROLL OVER VALVE
AUXILIARY TANK FILLER NECK
FUEL QUANTITY TRANSMITTER
FUEL VENT LINE
AUXILIARY FUEL TANK
FUEL TRANSFER LINE
FUEL TRANSFER LINE
FUEL LEVEL CONTROL VALVE
MAIN FUEL TANK (REF.)
SUPPLEMENTAL FUEL SYSTEM INSTALLATION
STA 230.5 BULKHEAD
VENT ROLLOVER VALVE AUX FUEL PORT
CHECK VALVE
CABIN FLOOR (REF)
BAGGAGE
(REF.)
FUEL TRANSFER LINE
COMPARTMENT
FLOOR
VENT/ROLLOVER VALVE
VENT LINE
FUEL TRANSFER LINE
MAIN FUEL TANK
(REF)
GRAVITY FILL PORT
LEVEL CONTROL VALVE
CHECK VALVE
AFT RH VENT LINE
FLAME ARRESTOR
AUXILIARY FUEL TANK
NEW CHECK VALVE
(IF INSTALLED)
AFT VENT FAIRING
FUEL QUANTITY XMITTER FLOAT
TRANSFER PUMP
FUEL TANK DRAIN PLUG
FUEL TRANSFER LINE
(AUXILIARY FUEL TANK ROTATED 90° CW FOR CLARITY)
SUPPLEMENTAL FUEL SYSTEM SCHEMATIC
F90-158B
Figure 10−14. Supplemental Fuel System
10−34
FAA Approved
Reissue 3
Revision 1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
PART VIII
HANDLING SERVICING AND MAINTENANCE
Fuel additives:
Anti-icing additives, if required, must be added to the auxiliary fuel tank during
refueling.
FAA Approved
Reissue 3
Original
10−35
CSP−900RFM206A−1
Optional Equipment
Supplemental Fuel System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−36
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
10−10. OPERATING INSTRUCTIONS: RESCUE HOIST
PART I
GENERAL
The rescue hoist system provides a means for lowering and raising personnel or
cargo from an airborne helicopter. It is capable of being operated from the passenger
cabin by a qualified crewmember or from the pilot's station.
PART II
LIMITATIONS
Type of operation:
Hoist operations shall be conducted under appropriate airworthiness and/or oper­
ating rules for external loads.
Minimum flight crew:
Pilot, when conducting operations with hoist stowed.
Pilot and hoist operator, when conducting hoist operations.
NOTE: Hoist operator must wear appropriate safety gear, safety harness, and have
voice communications with the pilot during hoist operations.
Weight and balance:
Maximum lateral CG limit at 60 KIAS or less:
+9.0 IN at 5550 LB gross weight; +7.5 IN at 6500 LB gross weight.
At airspeeds above 60 KIAS, normal CG limits apply.
CAUTION
With hoist installed, lateral C.G. may be exceeded with fuel
consumption. Flight planning should include a minimum fuel lateral
C.G. check.
FAA Approved
Reissue 3
Original
10−37
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
Airspeed limitations:
Observe airspeed limitations in Section II with hoist installed and doors closed.
Observe VNE for doors open/removed flight in Section II.
VNE while conducting hoist operations is 60 KIAS.
Hoist limitations:
Maximum load on hoist is 600 LB.
Maximum permissible cable deflection is 15° with respect to the aircraft vertical
axis.
During normal flight operations and airspeeds above 60 KIAS, the cable/hook
must be in the fully raised position.
Center of gravity limitations:
CAUTION
Size, weight, shape of load and cable length may affect flight
characteristics.
6500
MAXIMUM LATERAL CG
LIMIT AT 60 KIAS OR LESS:
+9.0 IN AT 5550 LB GROSS
WEIGHT; +7.5 IN AT 6500 LB
GROSS WEIGHT.
WEIGHT − POUNDS
6000
5500
5000
4500
4000
3500
3000
−3
−2
−1
0
1
2
3
4
5
LATERAL C.G. STATION (IN.)
6
7
8
9
10
F92-179A
Figure 10−15. Center of Gravity Envelope for Hoist Operations Below 60 KIAS
10−38
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
CABLE CUTTING:
Procedures:
Pilot: Activate the CABLE CUT switch on collective to jettison load in the
event of an emergency.
Hoist operator: Use provided cable cutters.
GENERATOR FAILURE:
NOTE: Hoist operations can require up to 125 amps of electrical power (63% load from
one generator).
Procedures:
Monitor operating generator load and turn off unnecessary electrical
equipment if required to maintain generator load within limits. Allowing
a GENERATOR HIGH LOAD condition to exist will result in the
operating generator going off line.
ADVISORY INDICATIONS:
Indications: Green or yellow indicator light (located on control pendant) - steady green
or yellow
Indications:
Conditions: Motor overtemperature.
NOTE: The light will remain on until the motor has cooled or electrical power to the
controller is switched off.
Procedures: Complete hoist operation in progress.
CAUTION
Prolonged operation of hoist with motor overtemperature light
illuminated will result in damaged or a ‘‘burned out’’ motor.
Indications: Flashing green light and a reduction of hoist speed.
Conditions: Hoist load above 250 LB with load mode select switch set to 250.
Procedures: Reduce hoist load or place load mode select switch to 600.
FAA Approved
Reissue 3
Original
10−39
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART IV
NORMAL PROCEDURES
Preflight checks:
CAUTION
To lower the work platforms/steps, remove the quick release pin
on the hoist strut and move the strut aside. The quick release pin
must be reinstalled before any load is placed on the hoist.
NOTE: External power is required for functional checks.
Rescue hoist assembly
CHECK − FOR OIL
LEAKS AND GENERAL
CONDITION
Hoist fairing
CONDITION AND
SECURITY
Electrical connections
CHECK
Hook assembly - freeness of swivel and latch
CHECK
Hoist support tube
CHECK MOUNTING
Hoist strut
CHECK MOUNTING AND
QUICK RELEASE PIN
Pendant control - electrical connection
CHECK
HOIST PWR and HOIST CUT circuit breakers
IN
Pilot's hoist control panel
CHECK SWITCH OFF
Electrical Master Panel
BAT/EXT
Power switch
Pilot's Hoist Control
Hoist arming switch
ON
Hoist armed light - on
CHECK
Payout displays
CHECK
Hoist operational check (pilot and operator)
CHECK
CAUTION
10−40
Do not restrict cable payout during this check. Fouling of the cable
on the drum will result if this precaution is not followed.
Reel out approximately 25 feet (8 meters) or more of
cable by using both the pendant and the pilot payout
controls. Do not exceed 15° cable deflection
FAA Approved
Reissue 3
Original
OPERATE HOIST
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
NOTE: The cable should be reeled out onto a smooth, clean surface or payed out into
a drum. Exercise care to prevent kinking of the cable.
Reel in cable by using both the pendant and the pilot
payout controls and verify hoist stops when hook
reaches upper limit without excess tension on cable.
Verify that pilot's pay out switch overrides hoist oper­
ator's pendant control
OPERATE HOIST
NOTE: It is important that the cable be reeled in with an even pull under a drag load of
10 to 20 LB so that it does not wrap loosely on the drum. A drag load must be
applied using a gloved hand or clean heavy cloth on the cable to achieve tight,
even layers on the drum.
OFF
Hoist arming switch
Electrical Master Panel:
OFF
Power switch
Hoist operation:
WARNING
Hoist operator must wear appropriate safety gear, safety harness,
and have voice communications with the pilot during hoist
operations.
NOTE: Operation of the pilot’s payout switch overrides the hoist operator.
Hoist arming switch
ON
Stabilize the aircraft in a hover over area
ESTABLISH
Cabin door (if closed)
OPEN
Hoist operator select load mode
250 OR 600 LB
Payout control switch
DOWN
NOTE: If possible, ensure that the helicopter has been electrically grounded prior to
attaching cargo to drain static electricity that may build up in flight.
UP
Payout control switch
Maintain hover until load is inside passenger cabin unless safety or operational
conditions dictate otherwise.
NOTE: Certain combinations of weight and cable length may induce a noticeable
lateral oscillation. Should a lateral oscillation occur, raise or lower the load to
alleviate this condition.
FAA Approved
Reissue 3
Original
10−41
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
MOTOR
WRN
INDICATOR
LIGHT
ÔÔ
ÔÔ
ÔÔ
ÔÔ
ÔÔ
CABLE PAYOUT DISPLAY
FEET
UP
106
DN
HOIST
PAYOUT
DIRECTION/SPEED
CONTROL
LOAD MODE SELECT
6
0
0
OFF
2
5
0
MOTOR
UP
WRN
OFF
LB
ÔÔ
ÔÔ
ÔÔ
ÔÔ
ÔÔ
DN
HOIST
METERS
25
6
0
0
2
5
0
LB
EMERGENCY CABLE CUT
EMERGENCY CABLE CUT
PUSHBUTTON SWITCH
CABLE
CUT
ICS CONTROL SWITCH
LATEST
CONFIGURATION
CABLE CUT
UP
H
O
I
S
DN T
HOIST OPERATOR'S CONTROL
PENDANT ASSEMBLY
PILOT'S PAYOUT
CONTROL SWITCH
25
CABLE PAYOUT
METERS
T/O
TIMER
COLLECTIVE CONTROL
MODULE (REF)
NOTE: LOCATIONS OF PILOT'S HOIST POWER SWITCH/ARMED LIGHT AND HOIST
POWER SWITCH/ARMED INDICATOR VARY WITH INSTALLED OPTIONS.
BAGGAGE COMPARTMENT MOUNTED
CIRCUIT BREAKER PANEL
HOIST ARMING SWITCH
ON
106
CABLE PAYOUT
FEET
HOIST
PWR
OFF
HOIST
PILOT'S HOIST CONTROL
HOIST POWER SWITCH/ARMED
INDICATOR
LATEST CONFIGURATION
HOIST ARMED LIGHT
Figure 10−16. Rescue Hoist Controls
10−42
FAA Approved
Reissue 3
Original
HOIST
CUT
HOIST
PWR
RESCUE HOIST
CIRCUIT BREAKERS
F927−058B
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
PART V
PERFORMANCE DATA
CAUTION
Reduce hover gross weight capability 70 LB when hovering with
rescue hoist installed.
Refer to Section V for hover performance data.
PART VI
WEIGHT AND BALANCE DATA
Maximum operating and hoist load weights:
Maximum gross weight for hoist operations is 6500 LB including hoist load.
Maximum load on the hoist is 600 LB. This is a structural limit and does not
assure loading within approved limits. Maximum allowable hoist load changes
with gross weight and aircraft CG. Refer to Figure 10-17 to determine maximum
allowable hoist load.
ITEM
WEIGHT
STATION (ARM)
MOMENT
Lateral
Longitudinal
Lateral
Longitudinal
Hoist installation
136.8
55.60
199.1
7611
27231
Hoist Load
−−−−−
59.25
199.1
−−−−−
−−−−−
Hoist lateral CG determination:
The following examples show a minimum crew of pilot and hoist operator. Notice
that in Example I, the helicopter is enroute (above 60 KIAS) and the hoist operator
is stationed in the left rear facing seat, thereby maintaining the lateral CG limit
of "2 IN.
In Example II, the helicopter is at the destination (below 60 KIAS) and the hoist
operator moves to the right of the aircraft cabin and stands on step.
Example III shows CG with a load on the hoist.
FAA Approved
Reissue 3
Original
10−43
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
EXAMPLE I: Lateral CG Determination − Enroute (above 60 KIAS)
WEIGHT
(LB)
ITEM
Basic Weight
STATION
(ARM)
MOMENT
(IN−LB)
3272.8
Hoist Installation
1465
136.8
55.60
7611
Pilot
200
15.85
3170
Hoist Operator (L/H seat)
200
-19.00
-3800
Fuel
700
0.00
0
Gross Weight
4509.6
8446
Calculation of Lateral CG:
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
=
8446
4509.6
= 1.90
EXAMPLE II: Lateral CG Determination − Destination (below 60 KIAS)
WEIGHT
(LB)
ITEM
Basic Weight
STATION
(ARM)
3272.8
Hoist Installation
MOMENT
(IN−LB)
1465
136.8
55.60
7611
Pilot
200
15.85
3170
Hoist Operator (R/H step)
200
35.00
7000
Fuel
400
0.00
0
Gross Weight
4209.6
19246
Calculation of Lateral CG:
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
10−44
=
19246
4209.6
FAA Approved
Reissue 3
Original
= 4.60
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
EXAMPLE III: Lateral CG Determination − With Hoist Load
WEIGHT
(LB)
ITEM
Basic Weight
STATION
(ARM)
3272.8
MOMENT
(IN−LB)
1465.0
Hoist Installation
136.8
55.60
7611.0
Pilot
200.0
15.85
3170.0
Hoist Operator (R/H step)
200.0
35.00
7000.0
Hoist load
250.0
59.25
14812.5
Fuel
400.0
0.00
0
Gross Weight
4409.6
34058.5
Calculation of Lateral CG:
CG at Gross Weight:
Moment at Gross Weight
Gross Weight
=
34058.5
4409.6
FAA Approved
Reissue 3
Original
= 7.72
10−45
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
HELICOPTER GROSS WEIGHT (LB) - WITHOUT HOIST LOAD
Optional Equipment
Rescue Hoist
6500
6400
6300
6200
6100
6000
5900
5800
5700
5600
5500
5400
5300
5200
5100
5000
4900
4800
4700
4600
4500
4400
4300
4200
4100
4000
3900
100 LB
200 LB
300 LB
400 LB
500 LB
600 LB
FOR USE BELOW
60 KIAS ONLY
MAXIMUM
HOIST LOAD
0.0
0.5
1.0
1.5
2.0
2.5
3.0
3.5
4.0
4.5
5.0
5.5
6.0
6.5
7.0
7.5
8.0
HELICOPTER LATERAL STGATION CG (IN) - WITHOUT HOIST LOAD
8.5
9.0
F92-178A
Figure 10−17. Allowable Rescue Hoist Loading Chart
Use of chart:
Use Figure 10-17 to determine the maximum hoist load for this operation.
Example:
Known:
From EXAMPLE II:
lateral CG = 4.6 inches
gross weight = approximately 4210 LB.
Enter chart at the ``Helicopter Gross Weight Without Hoist Load'' scale at 4210
pounds and proceed horizontally to intersect with a line drawn vertically from
the ``Helicopter Lateral Station Without Hoist Load'' scale at 4.6 IN. Where the
two lines intersect is the allowable hoist load. For this example the allowable
hoist load is approximately 369 pounds.
10−46
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
PART VII
SYSTEM DESCRIPTION
The hoist assembly consists of a cable drum that holds 245 feet (75.7 meters) of
3/16” in. (5 millimeter) spin resistant cable, a fail safe load brake, 28 VDC electric
motor, limit switches coupled to the cable drum to control fully-extended and inter­
mediate cable positions, and redundant switches. The hoist installation is mounted
to the airframe by a support tube and strut assembly (Ref. Figure 10-18).
Hoist speed control is accomplished by a command applied to either the variable
speed switch on the hoist operator's control pendant or the constant speed switch
located on the collective control module. With the load selection switch set at 250,
cable speed is 225 feet (68.5 meters) per minute. With the load selection switch
set at 600, cable speed is 100 feet (30.5 meters) per minute (Ref. Figure 10-16).
If the load select switch is set at 250 and the hoist load is above 250 LB, a flashing
warning light will illuminate and the hoist speed will automatically be reduced
to 100 feet (30.5 meters) per minute.
The controller also passes cable position information from the hoist. This position
information is absolute and will continue to provide cable position information if
power is interrupted.
The pilot's payout switch overrides the hoist operator. When the pilot operates the
payout switch, the hoist is automatically set to the 600 LB 100 feet (30.5 meters)
per minute mode.
Additional information pertaining to the hoist installation may be found in the
Breeze-Eastern Corp. manual TD-92-015.
FAA Approved
Reissue 3
Original
10−47
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
HOIST ASSEMBLY
(FAIRING REMOVED)
VARIABLE SPEED
CONTROLLER
É
HOOK
CONTROL
PENDANT
MID SKID GUARD
HOIST SUPPORT ASSEMBLY ROTATED
FAIRING
HAND HOLD
(OPTIONAL)
SUPPORT
TUBE
15°
15°
WHITE
STRIPE
AFT SKID TUBE
COVER
MID SKID
GUARD
WHITE
STRIPE
STRUT
INBOARD
AFT
FWD SKID TUBE
COVER
F92−177A
Figure 10−18. Rescue Hoist Installation
10−48
FAA Approved
Reissue 3
Original
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Rescue Hoist
PART VIII
HANDLING SERVICING AND MAINTENANCE
Table 10−6. Servicing Materials
Specification
Material
Manufacturer
Hoist assembly:
MIL-L-7808
Stauffer Jet I
Stauffer Chemical Co.
380 Madison Avenue
New York, NY 10017
American PQ
Lubricant 6899
American Oil and
Supply Co.
Mobil Avrex S
Turbo 256
Mobil Oil Co.
Brayco 880H
Bray Oil Co
1925 Marianna Street
Los Angeles, CA 90032
Exxon Turbo
Oil 2389
Exxon Co.
FAA Approved
Reissue 3
Original
10−49
CSP−900RFM206A−1
Optional Equipment
Rescue Hoist
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−50
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Dash 111/117 IIDS
10−11. OPERATING INFORMATION: −111/−117 IIDS OPTION
PART I
GENERAL
The -111 and -117 IIDS option allow for increased OEI torque limits.
NOTE: The −117 IIDS replaces the −111 IIDS following completion of SB 900−081R1 or
later.
PART II
LIMITATIONS
OEI limits:
Maximum continuous: 124%
2.5 minute: 125% to 130%
Torque greater than 130%: NOT ALLOWED
TORQUE
>130%
>124%
>122%
EEC
MAN
FAIL
F90−175
Figure 10−19. OEI Engine Torque Display
FAA Approved
Reissue 3
Original
10−51
CSP−900RFM206A−1
Optional Equipment
Dash 111/117 IIDS
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART V
PERFORMANCE DATA
20000
19000
18000
17000
16000
-36°C
OAT°C
15000
-30°C
14000
PRESSURE ALTITUDE - FEET
13000
-20°C
12000
11000
-10°C
10000
0°C
9000
10°C
8000
7000
20°C
6000
30°C
5000
4000
40°C
3000
2000
1000
0
-600
MAXIMUM
OAT LIMIT
-500
50°C
-400
-300
-200
-100
0
100
200
300
400
500
600
RATE OF CLIMB AT VY - FT/MIN
F90-180
Figure 10−20. Single Engine Rate of Climb and Descent at VY, OEI MCP
6250 LBS Gross Weight
10−52
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Fire Extinguishing System
10−12. OPERATING INSTRUCTIONS: FIRE EXTINGUISHING SYSTEM
PART I
GENERAL
The fire extinguishing system provides a means for the pilot to direct a charge
of fire extinguishing agent into the designated fire zone of each engine. There is
no fire extinguishing system for the transmission area.
PART II
LIMITATIONS
No change
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
Refer to Section III, paragraph for fire emergencies.
EXTINGUISHER PRESSURE LOW
Indications: EXTNGSHR PRESS LO message on IIDS alphanumeric display
Conditions: Low pressure in Halon containers
Procedures: Advise maintenance
FAA Approved
Reissue 3
Original
10−53
CSP−900RFM206A−1
Optional Equipment
Fire Extinguishing System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
PART IV
NORMAL PROCEDURES
No change.
PART V
PERFORMANCE DATA
No change.
PART VII
SYSTEM DESCRIPTION
The fire extinguishing system (Ref. Figure 10-21) contains two individual hermeti­
cally sealed pressurized spherical containers (bottles) that are filled with 60 cubic
inches of CF3 BR (Bromotrifluoromethane), also known as Halon 1301, and pressur­
ized with nitrogen gas to an internal pressure of 700 PSIG. Each bottle serves as
the primary bottle for its appropriate side engine.
Each bottle is equipped with dual outlet ports, a pressure gauge with electrical
low pressure warning signal to IIDS, filler port and thermal relief valve. The outlets
ports are fitted with electrically discharged explosive squibs. The fire extinguisher
cartridges are armed and ready for firing when the fuel shutoff valves are placed
in the OFF (closed) position. The bottles are discharged when the BOTTLE DIS­
CHARGE switch is momentarily placed in the PRI (primary) or ALT (alternate)
position.
The BOTTLE DISCHARGE switch is a momentary type, three position switch located
between the left and right fuel shutoff valves on the cockpit FUEL SYSTEM panel.
Placing a fuel shutoff valve OFF arms the fire extinguishing system for that engine
and selection of PRI discharges its primary bottle. Selection of ALT discharges the
second bottle onto the same engine.
10−54
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Fire Extinguishing System
PRESSURE GAUGE
FILLER PORT
(RED PORT)
PRIMARY
CARTRIDGE
(BLUE PORT)
ALTERNATE
CARTRIDGE
DISCHARGE TUBE
DISCHARGE TUBE
DISTRIBUTION TUBE
RIGHT SIDE
REF
ENGINE DECK
FIRE BOTTLE
ASSEMBLY
DISTRIBUTION TUBE
LEFT SIDE
OUTLET
PORT
CROSS FLOW
TUBES
OUTLET
PORT
FUEL SYSTEM
L BOOST
CROSS FEED
ON
OFF
R BOOST
ON
ON
OFF
OFF
FUEL SHUTOFF
FIRE EXTINGUISHER
BOTTLE DISCHARGE
SWITCH
BOTTLE
DISCHARGE
PRI
O
F
F
ALT
LEFT OFF
RIGHT OFF
F90−126
Figure 10−21. Fire Extinguishing System
FAA Approved
Reissue 3
Original
10−55
CSP−900RFM206A−1
Optional Equipment
Fire Extinguishing System
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−56
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Smoke Detector
10−13. OPERATING INSTRUCTIONS: SMOKE DETECTOR
PART I
GENERAL
No change.
PART II
LIMITATIONS
No change.
PART III
EMERGENCY AND MALFUNCTION PROCEDURES
CARGO COMPARTMENT FIRE/SMOKE
Indications: Smoke detector warning tone in headset.
Conditions: On ground
Procedures:
Engine control switches
OFF
Passengers/crew
EVACUATE
Rotor brake (if installed)
APPLY
Power switch
OFF
Conditions: In flight
Procedures:
Fresh air vents
OPEN
AC/VENT switch
VENT LOW OR VENT HIGH
Cockpit door vents
OPEN
Land immediately
FAA Approved
Reissue 3
Original
10−57
CSP−900RFM206A−1
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
Optional Equipment
Smoke Detector
After landing:
Engine control switches
OFF
Rotor brake (if installed)
APPLY
Power switch
OFF
Passengers/crew
EVACUATE
PART IV
NORMAL PROCEDURES
PRE FLIGHT CHECKS: ELECTRICAL POWER ON
Baggage compartment:
Circuit breaker panel cover
REMOVE
SMOKE DET press-to-test button
PRESS
Listen for smoke detector warning tone in
headset.
CHECK
NOTE: A second crew member is required to perform this check.
Circuit breaker panel cover
RH REAR FUSELAGE
SHELL ASSEMBLY
SMOKE
DETECTOR
REPLACE
BAGGAGE COMPARTMENT­
CIRCUIT BREAKER PANEL
HDG
SAS/AP
ADF
26 VAC BUS
RIGHT AVIONICS BUS
ADF1
FM
CTRL
FM1
RT
FM2
RT
DME
STORM
SCOPE
CAMERA
NAV 1
FM3
RT
RMI
PRESS TO
TEST
SMOKE
DET
F927−118
Figure 10−22. Smoke Detector and Press−To−Test Switch Location.
10−58
FAA Approved
Reissue 3
Original
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
CSP−900RFM206A−1
Optional Equipment
Smoke Detector
PART V
PERFORMANCE DATA
No change.
PART VII
SYSTEM DESCRIPTION
The smoke detector is a photoelectric device specifically developed for aircraft cargo
bay applications and is located on the upper right hand wall of the baggage compart­
ment adjacent to the baggage compartment door. The detector incorporates specific
design features that virtually eliminate the reliability problems typically associated
with aircraft smoke detectors. The detector is a dual-channel, ratio-comparing de­
vice in which one channel detects the presence of smoke and the second channel
serves as a reference. By comparing smoke and reference ratios, the detector is
able to operate reliably despite dust, moisture, temperature changes, and aging.
The detector provides an alarm signal (sweeping tone) to the aircraft ICS system
when the output from the smoke channel exceeds a predetermined ratio to the output
from the reference channel. The warning tone is heard through the headset. A test
input activates a complete through-the-lens check of electronic and optical func­
tions. The press-to-test button is located on the lower right hand corner of the
right avionics bus.
The smoke detector system receives power from the battery bus and is protected
by a 5 amp. circuit breaker.
FAA Approved
Reissue 3
Original
10−59
CSP−900RFM206A−1
Optional Equipment
Smoke Detector
ROTORCRAFT FLIGHT MANUAL
MD900 with PW 206A
This page intentionally left blank!
10−60
FAA Approved
Reissue 3
Original