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JZ-Y8F200W-02
Y8F200W AIRCRAFT
AIRCRAFT FLIGHT MANUAL
China National Aero-Technology Import & Export Corporation
June 30, ...
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AIRCRAFT FLIGHT MANUAL
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TABLE OF SERVICE BULLETINS
BULLETIN NO. AMEND. MARKS D...
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TOC
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June 30, 2012
Table of Contents
SUBJECT PAGE
GENERAL..............................
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TOC
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SUBJECT PAGE
NORMAL PROCEDURES......................................
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SUBJECT PAGE
Signal, Illuminating apparatus...............
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SECTION I
GENERAL
1-1
June 30, 2012
GENERAL
INTRODUCTION
Y8F200W is the multifunction...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-2
June 30, 2012
The tricycle landing gears are of retractable/ext...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-3
June 30, 2012
The aircraft is equipped with anti-icing device. ...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-4
June 30, 2012
The airborne navigation system mainly includes HG...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-5
June 30, 2012
AIRCRAFT TECHNICAL DATA
Principal geometrical dat...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-6
June 30, 2012
(k) Boarding gate dimension
Height × width 4.77 f...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-7
June 30, 2012
(p) Flap deflection angle
Takeoff 15o
~(25±1)o
La...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-8
June 30, 2012
(s) Max. deflection angle of rudder trim tab Left...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-9
June 30, 2012
(j) Parking compression of aircraft tyre
Parking ...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-10
June 30, 2012
(j) Engine data in different operating condition...
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AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-11
June 30, 2012
(h) Full feathering position time
Engine operati...
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AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-12
June 30, 2012
Turbo starter generator
(a) Power rate (at the t...
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AIRCRAFT FLIGHT MANUAL
SECTION I
GENERAL
1-13/(14 Blank)
June 30, 2012
AIRCRAFT THREE-VIEW ARRANGEMENT
For d...
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SECTION I
GENERAL
1-14
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SECTION II
OPERATIONAL LIMITATION
2-1
June 30, 2012
OPERATIONAL LIMITATION
GENERAL OF...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-2
June 30, 2012
SPEED LIMITATIONS
(a) Speed limit...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-3
June 30, 2012
(c) Speed limitation polar curve ...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-4
June 30, 2012
(d) Speed and Mach number limit f...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-5
June 30, 2012
(l) Max. maneuver speed of level ...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-6
June 30, 2012
H(ft)
3281
24606
16404
8202
108 2...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-7
June 30, 2012
WEIGHT AND C.G. LIMITATIONS
Basic...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-8
June 30, 2012
Fuel quantity limitation for typi...
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SECTION II
OPERATIONAL LIMITATION
2-9
June 30, 2012
RelativeC.Goftheaircraft(%CA
) C....
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-10
June 30, 2012
RelativeC.Goftheaircraft(%CA
)
C...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-11
June 30, 2012
RelativeC.Goftheaircraft(%CA) C....
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-12
June 30, 2012
60000 55000 50000 45000 40000 35...
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SECTION II
OPERATIONAL LIMITATION
2-13
June 30, 2012
60000 55000 50000 45000 40000 35...
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SECTION II
OPERATIONAL LIMITATION
2-14
June 30, 2012
60000 55000 50000 45000 40000 35...
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SECTION II
OPERATIONAL LIMITATION
2-15
June 30, 2012
G-LOAD LIMITATION
(a) Upon takeo...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-16
June 30, 2012
LIMITATIONS OF POWER PLANT
(a) E...
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SECTION II
OPERATIONAL LIMITATION
2-17
June 30, 2012
(c) Engine operational limitatio...
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AIRCRAFT FLIGHT MANUAL
SECTION II
OPERATIONAL LIMITATION
2-18
June 30, 2012
Table 2-8b Allowable bleed rate ...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-1
June 30, 2012
EMERGENCY PROCEDURES
Various speci...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-2
June 30, 2012
Engine failures during takeoff
Onc...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-3
June 30, 2012
(c) Judge propeller feathering sta...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-4
June 30, 2012
(b) After any one of the four engi...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-5
June 30, 2012
Air start of the engine
(a) Only w...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-6
June 30, 2012
3) When turbine exhaust temperatur...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-7
June 30, 2012
(g) Two engines fail at the same s...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-8
June 30, 2012
4) When flying horizontally at the...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-9
June 30, 2012
6) When the running speed is lower...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-10
June 30, 2012
4) In order to reduce the rudder ...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-11
June 30, 2012
4) When the propeller of an outbo...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-12
June 30, 2012
(k) Landing procedures with an ou...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-13
June 30, 2012
b) If an inboard engine fails and...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-14
June 30, 2012
b) To prevent the high-pressure f...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-15
June 30, 2012
d) Feather the failed engine with...
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AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-16
June 30, 2012
HIGH ANGLE OF ATTACK FLIGHT
The a...
JZ-Y8F200W-02
AIRCRAFT FLIGHT MANUAL
SECTION III
EMERGENCY PROCEDURES
3-17
June 30, 2012
The symptoms of the aircraft stal...
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Aircraft flight manual
Aircraft flight manual
Aircraft flight manual
Aircraft flight manual
Aircraft flight manual
Aircraft flight manual
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Aircraft flight manual

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  1. 1. JZ-Y8F200W-02 Y8F200W AIRCRAFT AIRCRAFT FLIGHT MANUAL China National Aero-Technology Import & Export Corporation June 30, 2012
  2. 2. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL ROR 1/(2 Blank) June 30, 2012 RECORD OF REVISIONS REV. NO. REV. DATE INSERTION REV. NO. REV. DATE INSERTION DATE BY DATE BY
  3. 3. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL ROR 2 June 30, 2012 THIS PAGE INTENTIONALLY LEFT BLANK
  4. 4. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL ROTR 1/(2 Blank) June 30, 2012 RECORD OF TEMPORARY REVISIONS TEMPORARY REV. INSERTION DELETION REV. NO. PAGE NO. DATE ISSUED DATE BY DATE REV. NO. BY
  5. 5. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL ROTR 2 June 30, 2012 THIS PAGE INTENTIONALLY LEFT BLANK
  6. 6. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOSB 1/(2 Blank) June 30, 2012 TABLE OF SERVICE BULLETINS BULLETIN NO. AMEND. MARKS DATE DESCRIPTION
  7. 7. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOSB 2 June 30, 2012 THIS PAGE INTENTIONALLY LEFT BLANK
  8. 8. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 1 Jun. 30, 2012 LIST OF EFFECTIVE PAGES TOTAL NUMBER OF PAGES IS 748, CONSISTING OF THE FOLLOWING SUBJECT PAGE DATE SUBJECT PAGE DATE Title Page T-1 Jun. 30, 2012 Record of Revisions ROR-1 Jun. 30, 2012 ROR-2(Blank) Jun. 30, 2012 Record of ROR-1 Jun. 30, 2012 Temporary Revisions ROR-2(Blank) Jun. 30, 2012 Table of Service TOSB-1 Jun. 30, 2012 Bulletins TOSB-2(Blank) Jun. 30, 2012 List of Effective LEP 1 Jun. 30, 2012 Pages LEP 2(Blank) Jun. 30, 2012 Contents 1 Jun. 30, 2012 2 Jun. 30, 2012 Section 1 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14(Blank) Jun. 30, 2012 Section 2 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 17 Jun. 30, 2012 18 Jun. 30, 2012 Section 3 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 17 Jun. 30, 2012 18 Jun. 30, 2012 19 Jun. 30, 2012 20 Jun. 30, 2012 21 Jun. 30, 2012 22 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  9. 9. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 2 June 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 23 Jun. 30, 2012 24 Jun. 30, 2012 25 Jun. 30, 2012 26 Jun. 30, 2012 27 Jun. 30, 2012 28 Jun. 30, 2012 29 Jun. 30, 2012 30 Jun. 30, 2012 31 Jun. 30, 2012 32 Jun. 30, 2012 Section 4 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 17 Jun. 30, 2012 18 Jun. 30, 2012 19 Jun. 30, 2012 20 Jun. 30, 2012 21 Jun. 30, 2012 22 Jun. 30, 2012 23 Jun. 30, 2012 24 Jun. 30, 2012 25 Jun. 30, 2012 26 Jun. 30, 2012 27 Jun. 30, 2012 28 Jun. 30, 2012 29 Jun. 30, 2012 30 Jun. 30, 2012 31 Jun. 30, 2012 32 Jun. 30, 2012 33 Jun. 30, 2012 34 Jun. 30, 2012 35 Jun. 30, 2012 36 Jun. 30, 2012 37 Jun. 30, 2012 38 Jun. 30, 2012 39 Jun. 30, 2012 40 Jun. 30, 2012 41 Jun. 30, 2012 42 Jun. 30, 2012 43 Jun. 30, 2012 44 Jun. 30, 2012 45 Jun. 30, 2012 46 Jun. 30, 2012 47 Jun. 30, 2012 48 Jun. 30, 2012 49 Jun. 30, 2012 50 Jun. 30, 2012 51 Jun. 30, 2012 52 Jun. 30, 2012 53 Jun. 30, 2012 54 Jun. 30, 2012 55 Jun. 30, 2012 56 Jun. 30, 2012 57 Jun. 30, 2012 58 Jun. 30, 2012 59 Jun. 30, 2012 60 Jun. 30, 2012 61 Jun. 30, 2012 62 Jun. 30, 2012 63 Jun. 30, 2012 64 Jun. 30, 2012 65 Jun. 30, 2012 66 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  10. 10. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 3 Jun. 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 67 Jun. 30, 2012 68 Jun. 30, 2012 69 Jun. 30, 2012 70 Jun. 30, 2012 71 Jun. 30, 2012 72 Jun. 30, 2012 73 Jun. 30, 2012 74 Jun. 30, 2012 75 Jun. 30, 2012 76 Jun. 30, 2012 77 Jun. 30, 2012 78 Jun. 30, 2012 79 Jun. 30, 2012 80 Jun. 30, 2012 81 Jun. 30, 2012 82 Jun. 30, 2012 83 Jun. 30, 2012 84 Jun. 30, 2012 85 Jun. 30, 2012 86 Jun. 30, 2012 87 Jun. 30, 2012 88 Jun. 30, 2012 89 Jun. 30, 2012 90 Jun. 30, 2012 91 Jun. 30, 2012 92 Jun. 30, 2012 93 Jun. 30, 2012 94 Jun. 30, 2012 95 Jun. 30, 2012 96 Jun. 30, 2012 97 Jun. 30, 2012 98 Jun. 30, 2012 99 Jun. 30, 2012 100 Jun. 30, 2012 101 Jun. 30, 2012 102 Jun. 30, 2012 103 Jun. 30, 2012 104 Jun. 30, 2012 105 Jun. 30, 2012 106 Jun. 30, 2012 107 Jun. 30, 2012 108 Jun. 30, 2012 109 Jun. 30, 2012 110 Jun. 30, 2012 111 Jun. 30, 2012 112 Jun. 30, 2012 113 Jun. 30, 2012 114 Jun. 30, 2012 115 Jun. 30, 2012 116 Jun. 30, 2012 117 Jun. 30, 2012 118 Jun. 30, 2012 119 Jun. 30, 2012 120 Jun. 30, 2012 121 Jun. 30, 2012 122 Jun. 30, 2012 123 Jun. 30, 2012 124 Jun. 30, 2012 125 Jun. 30, 2012 126 Jun. 30, 2012 127 Jun. 30, 2012 128 Jun. 30, 2012 129 Jun. 30, 2012 130 Jun. 30, 2012 131 Jun. 30, 2012 132 Jun. 30, 2012 133 Jun. 30, 2012 134 Jun. 30, 2012 135 Jun. 30, 2012 136 Jun. 30, 2012 137 Jun. 30, 2012 138 Jun. 30, 2012 139 Jun. 30, 2012 140 Jun. 30, 2012 141 Jun. 30, 2012 142 Jun. 30, 2012 143 Jun. 30, 2012 144 Jun. 30, 2012 145 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  11. 11. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 4 June 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 146 Jun. 30, 2012 147 Jun. 30, 2012 148 Jun. 30, 2012 149 Jun. 30, 2012 150 Jun. 30, 2012 151 Jun. 30, 2012 152 Jun. 30, 2012 153 Jun. 30, 2012 154 Jun. 30, 2012 155 Jun. 30, 2012 156 Jun. 30, 2012 157 Jun. 30, 2012 158 Jun. 30, 2012 159 Jun. 30, 2012 160 Jun. 30, 2012 161 Jun. 30, 2012 162 Jun. 30, 2012 Section 5 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 17 Jun. 30, 2012 18 Jun. 30, 2012 19 Jun. 30, 2012 20 Jun. 30, 2012 21 Jun. 30, 2012 22 Jun. 30, 2012 23 Jun. 30, 2012 24 Jun. 30, 2012 25 Jun. 30, 2012 26 Jun. 30, 2012 27 Jun. 30, 2012 28 Jun. 30, 2012 29 Jun. 30, 2012 30 Jun. 30, 2012 31 Jun. 30, 2012 32 Jun. 30, 2012 33 Jun. 30, 2012 34 Jun. 30, 2012 35 Jun. 30, 2012 36 Jun. 30, 2012 37 Jun. 30, 2012 38 Jun. 30, 2012 39 Jun. 30, 2012 40 Jun. 30, 2012 Section 6 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 17 Jun. 30, 2012 18 Jun. 30, 2012 19 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  12. 12. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 5 Jun. 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 20 Jun. 30, 2012 21 Jun. 30, 2012 22 Jun. 30, 2012 23 Jun. 30, 2012 24 Jun. 30, 2012 25 Jun. 30, 2012 26 Jun. 30, 2012 27 Jun. 30, 2012 28 Jun. 30, 2012 29 Jun. 30, 2012 30 Jun. 30, 2012 31 Jun. 30, 2012 32 Jun. 30, 2012 33 Jun. 30, 2012 34 Jun. 30, 2012 35 Jun. 30, 2012 36 Jun. 30, 2012 37 Jun. 30, 2012 38 Jun. 30, 2012 39 Jun. 30, 2012 40 Jun. 30, 2012 41 Jun. 30, 2012 42 Jun. 30, 2012 43 Jun. 30, 2012 44 Jun. 30, 2012 45 Jun. 30, 2012 46 Jun. 30, 2012 47 Jun. 30, 2012 48 Jun. 30, 2012 49 Jun. 30, 2012 50 Jun. 30, 2012 51 Jun. 30, 2012 52 Jun. 30, 2012 53 Jun. 30, 2012 54 Jun. 30, 2012 55 Jun. 30, 2012 56 Jun. 30, 2012 57 Jun. 30, 2012 58 Jun. 30, 2012 59 Jun. 30, 2012 60 Jun. 30, 2012 61 Jun. 30, 2012 62 Jun. 30, 2012 63 Jun. 30, 2012 64 Jun. 30, 2012 65 Jun. 30, 2012 66 Jun. 30, 2012 67 Jun. 30, 2012 68 Jun. 30, 2012 69 Jun. 30, 2012 70 Jun. 30, 2012 71 Jun. 30, 2012 72 Jun. 30, 2012 73 Jun. 30, 2012 74 Jun. 30, 2012 75 Jun. 30, 2012 76 Jun. 30, 2012 77 Jun. 30, 2012 78 Jun. 30, 2012 79 Jun. 30, 2012 80 Jun. 30, 2012 81 Jun. 30, 2012 82 Jun. 30, 2012 83 Jun. 30, 2012 84 Jun. 30, 2012 85 Jun. 30, 2012 86 Jun. 30, 2012 87 Jun. 30, 2012 88 Jun. 30, 2012 89 Jun. 30, 2012 90 Jun. 30, 2012 91 Jun. 30, 2012 92 Jun. 30, 2012 93 Jun. 30, 2012 94 Jun. 30, 2012 95 Jun. 30, 2012 96 Jun. 30, 2012 97 Jun. 30, 2012 98 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  13. 13. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 6 June 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 99 Jun. 30, 2012 100 Jun. 30, 2012 101 Jun. 30, 2012 102 Jun. 30, 2012 103 Jun. 30, 2012 104 Jun. 30, 2012 105 Jun. 30, 2012 106 Jun. 30, 2012 107 Jun. 30, 2012 108 Jun. 30, 2012 109 Jun. 30, 2012 110 Jun. 30, 2012 111 Jun. 30, 2012 112 Jun. 30, 2012 113 Jun. 30, 2012 114 Jun. 30, 2012 115 Jun. 30, 2012 116 Jun. 30, 2012 117 Jun. 30, 2012 118 Jun. 30, 2012 119 Jun. 30, 2012 120 Jun. 30, 2012 121 Jun. 30, 2012 122 Jun. 30, 2012 123 Jun. 30, 2012 124 Jun. 30, 2012 125 Jun. 30, 2012 126 Jun. 30, 2012 127 Jun. 30, 2012 128 Jun. 30, 2012 129 Jun. 30, 2012 130 Jun. 30, 2012 131 Jun. 30, 2012 132 Jun. 30, 2012 133 Jun. 30, 2012 134 Jun. 30, 2012 135 Jun. 30, 2012 136 Jun. 30, 2012 137 Jun. 30, 2012 138 Jun. 30, 2012 139 Jun. 30, 2012 140 Jun. 30, 2012 141 Jun. 30, 2012 142 Jun. 30, 2012 143 Jun. 30, 2012 144 Jun. 30, 2012 145 Jun. 30, 2012 146 Jun. 30, 2012 147 Jun. 30, 2012 148 Jun. 30, 2012 149 Jun. 30, 2012 150 Jun. 30, 2012 151 Jun. 30, 2012 152 Jun. 30, 2012 153 Jun. 30, 2012 154 Jun. 30, 2012 155 Jun. 30, 2012 156 Jun. 30, 2012 157 Jun. 30, 2012 158 Jun. 30, 2012 159 Jun. 30, 2012 160 Jun. 30, 2012 161 Jun. 30, 2012 162 Jun. 30, 2012 163 Jun. 30, 2012 164 Jun. 30, 2012 165 Jun. 30, 2012 166 Jun. 30, 2012 167 Jun. 30, 2012 168 Jun. 30, 2012 169 Jun. 30, 2012 170 Jun. 30, 2012 171 Jun. 30, 2012 172 Jun. 30, 2012 173 Jun. 30, 2012 174 Jun. 30, 2012 175 Jun. 30, 2012 176 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  14. 14. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 7 Jun. 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 177 Jun. 30, 2012 178 Jun. 30, 2012 179 Jun. 30, 2012 180 Jun. 30, 2012 181 Jun. 30, 2012 182 Jun. 30, 2012 183 Jun. 30, 2012 184 Jun. 30, 2012 185 Jun. 30, 2012 186 Jun. 30, 2012 187 Jun. 30, 2012 188 Jun. 30, 2012 189 Jun. 30, 2012 190 Jun. 30, 2012 191 Jun. 30, 2012 192 Jun. 30, 2012 193 Jun. 30, 2012 194 Jun. 30, 2012 195 Jun. 30, 2012 196 Jun. 30, 2012 197 Jun. 30, 2012 198 Jun. 30, 2012 199 Jun. 30, 2012 200 Jun. 30, 2012 201 Jun. 30, 2012 202 Jun. 30, 2012 203 Jun. 30, 2012 204 Jun. 30, 2012 205 Jun. 30, 2012 206 Jun. 30, 2012 207 Jun. 30, 2012 208 Jun. 30, 2012 209 Jun. 30, 2012 210 Jun. 30, 2012 211 Jun. 30, 2012 212 Jun. 30, 2012 213 Jun. 30, 2012 214 Jun. 30, 2012 215 Jun. 30, 2012 216 Jun. 30, 2012 217 Jun. 30, 2012 218 Jun. 30, 2012 219 Jun. 30, 2012 220 Jun. 30, 2012 221 Jun. 30, 2012 222 Jun. 30, 2012 223 Jun. 30, 2012 224 Jun. 30, 2012 225 Jun. 30, 2012 226 Jun. 30, 2012 227 Jun. 30, 2012 228 Jun. 30, 2012 229 Jun. 30, 2012 230 Jun. 30, 2012 231 Jun. 30, 2012 232 Jun. 30, 2012 233 Jun. 30, 2012 234 Jun. 30, 2012 235 Jun. 30, 2012 236 Jun. 30, 2012 237 Jun. 30, 2012 238 Jun. 30, 2012 239 Jun. 30, 2012 240 Jun. 30, 2012 241 Jun. 30, 2012 242 Jun. 30, 2012 243 Jun. 30, 2012 244 Jun. 30, 2012 245 Jun. 30, 2012 246 Jun. 30, 2012 247 Jun. 30, 2012 248 Jun. 30, 2012 249 Jun. 30, 2012 250 Jun. 30, 2012 251 Jun. 30, 2012 252 Jun. 30, 2012 253 Jun. 30, 2012 254 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  15. 15. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 8 June 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 255 Jun. 30, 2012 256 Jun. 30, 2012 257 Jun. 30, 2012 258 Jun. 30, 2012 259 Jun. 30, 2012 260 Jun. 30, 2012 261 Jun. 30, 2012 262 Jun. 30, 2012 263 Jun. 30, 2012 264 Jun. 30, 2012 265 Jun. 30, 2012 266 Jun. 30, 2012 267 Jun. 30, 2012 268 Jun. 30, 2012 269 Jun. 30, 2012 270 Jun. 30, 2012 271 Jun. 30, 2012 272 Jun. 30, 2012 273 Jun. 30, 2012 274 Jun. 30, 2012 275 Jun. 30, 2012 276 Jun. 30, 2012 277 Jun. 30, 2012 278 Jun. 30, 2012 279 Jun. 30, 2012 280 Jun. 30, 2012 281 Jun. 30, 2012 282 Jun. 30, 2012 283 Jun. 30, 2012 284 Jun. 30, 2012 285 Jun. 30, 2012 286 Jun. 30, 2012 287 Jun. 30, 2012 288 Jun. 30, 2012 289 Jun. 30, 2012 290 Jun. 30, 2012 291 Jun. 30, 2012 292 Jun. 30, 2012 293 Jun. 30, 2012 294 Jun. 30, 2012 295 Jun. 30, 2012 296 Jun. 30, 2012 297 Jun. 30, 2012 298 Jun. 30, 2012 299 Jun. 30, 2012 300 Jun. 30, 2012 301 Jun. 30, 2012 302 Jun. 30, 2012 303 Jun. 30, 2012 304 Jun. 30, 2012 305 Jun. 30, 2012 306 Jun. 30, 2012 307 Jun. 30, 2012 308 Jun. 30, 2012 309 Jun. 30, 2012 300 Jun. 30, 2012 311 Jun. 30, 2012 312 Jun. 30, 2012 313 Jun. 30, 2012 314 Jun. 30, 2012 315 Jun. 30, 2012 316 Jun. 30, 2012 317 Jun. 30, 2012 318 Jun. 30, 2012 319 Jun. 30, 2012 320 Jun. 30, 2012 321 Jun. 30, 2012 322 Jun. 30, 2012 323 Jun. 30, 2012 324 Jun. 30, 2012 325 Jun. 30, 2012 326 Jun. 30, 2012 327 Jun. 30, 2012 328 Jun. 30, 2012 329 Jun. 30, 2012 330 Jun. 30, 2012 331 Jun. 30, 2012 332 Jun. 30, 2012 333 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  16. 16. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 9 Jun. 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE 334 Jun. 30, 2012 335 Jun. 30, 2012 336 Jun. 30, 2012 337 Jun. 30, 2012 338 Jun. 30, 2012 339 Jun. 30, 2012 340 Jun. 30, 2012 341 Jun. 30, 2012 342 Jun. 30, 2012 343 Jun. 30, 2012 344 Jun. 30, 2012 345 Jun. 30, 2012 346 Jun. 30, 2012 347 Jun. 30, 2012 348 Jun. 30, 2012 349 Jun. 30, 2012 350 Jun. 30, 2012 351 Jun. 30, 2012 352 Jun. 30, 2012 353 Jun. 30, 2012 354 Jun. 30, 2012 355 Jun. 30, 2012 356 Jun. 30, 2012 357 Jun. 30, 2012 358 Jun. 30, 2012 359 Jun. 30, 2012 360 Jun. 30, 2012 361 Jun. 30, 2012 362 Jun. 30, 2012 363 Jun. 30, 2012 364 Jun. 30, 2012 365 Jun. 30, 2012 366 Jun. 30, 2012 367 Jun. 30, 2012 368 Jun. 30, 2012 369 Jun. 30, 2012 370 Jun. 30, 2012 371 Jun. 30, 2012 372 Jun. 30, 2012 373 Jun. 30, 2012 374 Jun. 30, 2012 375 Jun. 30, 2012 376 Jun. 30, 2012 377 Jun. 30, 2012 378 Jun. 30, 2012 379 Jun. 30, 2012 380 Jun. 30, 2012 381 Jun. 30, 2012 382 Jun. 30, 2012 383 Jun. 30, 2012 384 Jun. 30, 2012 385 Jun. 30, 2012 386 Jun. 30, 2012 387 Jun. 30, 2012 388 Jun. 30, 2012 389 Jun. 30, 2012 390 Jun. 30, 2012 391 Jun. 30, 2012 392 Jun. 30, 2012 Appendix A A1 Jun. 30, 2012 A2 Jun. 30, 2012 A3 Jun. 30, 2012 A4 Jun. 30, 2012 A5 Jun. 30, 2012 A6 Jun. 30, 2012 A7 Jun. 30, 2012 A8 Jun. 30, 2012 A9 Jun. 30, 2012 A10 Jun. 30, 2012 A11 Jun. 30, 2012 A12 (Blank) Jun. 30, 2012 A13 Jun. 30, 2012 A14 (Blank) Jun. 30, 2012 A15 Jun. 30, 2012 A16 (Blank) Jun. 30, 2012 A17 Jun. 30, 2012 A18 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  17. 17. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL LEP 10 June 30, 2012 SUBJECT PAGE DATE SUBJECT PAGE DATE A19 Jun. 30, 2012 A20 Jun. 30, 2012 A21 Jun. 30, 2012 A22 Jun. 30, 2012 A23 Jun. 30, 2012 A24 Jun. 30, 2012 A25 Jun. 30, 2012 A26 Jun. 30, 2012 A27 Jun. 30, 2012 A28 Jun. 30, 2012 A29 Jun. 30, 2012 A30 Jun. 30, 2012 A31 Jun. 30, 2012 A32 (Blank) Jun. 30, 2012 A33 Jun. 30, 2012 A34 Jun. 30, 2012 A35 Jun. 30, 2012 A36 Jun. 30, 2012 A37 Jun. 30, 2012 A38 Jun. 30, 2012 Appendix B B1 Jun. 30, 2012 B2 Jun. 30, 2012 B3 Jun. 30, 2012 B4 Jun. 30, 2012 B5 Jun. 30, 2012 B6 Jun. 30, 2012 Appendix C C1 Jun. 30, 2012 C2 (Blank) Jun. 30, 2012 C3 Jun. 30, 2012 C4 (Blank) Jun. 30, 2012 Appendix D D1 Jun. 30, 2012 D2 (Blank) Jun. 30, 2012 GLOSSARY 1 Jun. 30, 2012 2 Jun. 30, 2012 3 Jun. 30, 2012 4 Jun. 30, 2012 5 Jun. 30, 2012 6 Jun. 30, 2012 7 Jun. 30, 2012 8 Jun. 30, 2012 9 Jun. 30, 2012 10 Jun. 30, 2012 11 Jun. 30, 2012 12 Jun. 30, 2012 13 Jun. 30, 2012 14 Jun. 30, 2012 15 Jun. 30, 2012 16 Jun. 30, 2012 F Foldout page, printed on single face D Deleted page R Revised page A Added page
  18. 18. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOC 1 June 30, 2012 Table of Contents SUBJECT PAGE GENERAL.......................................................................................................................................1  Introduction.............................................................................................................................1  Aircraft technical data .............................................................................................................5  Aircraft three-view arrangement ...........................................................................................13 OPERATIONAL LIMITATION ..........................................................................................................1  General of flight limitation .......................................................................................................1  Flight limitation........................................................................................................................1  Speed limitations ....................................................................................................................2  Weight and C.G. limitations.....................................................................................................7  G-load limitation....................................................................................................................15  Limitations of power plant.....................................................................................................16  Operational limitation for air conditioning system .................................................................18 EMERGENCY PROCEDURES ......................................................................................................1  Engine failures........................................................................................................................1  High angle of attack flight .....................................................................................................16  Flying with door open and descending in emergency...........................................................21  Landing with the malfunctioned landing gear system ...........................................................22  Handling of tyre blown-up and brakes failure........................................................................25  Handling of heading system and the barometer failed in flight .............................................26  Landing with flaps up............................................................................................................27  Outside forced landing..........................................................................................................29
  19. 19. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOC 2 June 30, 2012 SUBJECT PAGE NORMAL PROCEDURES..............................................................................................................1  Preparations for flight ............................................................................................................1  Flight ....................................................................................................................................25 PERFORMANCE ...........................................................................................................................1  General ..................................................................................................................................1  Aircraft flight performance calculation and conversion curve .................................................1  Main performance of four engines..........................................................................................7  Main performance of three engines......................................................................................15  Takeoff and landing performance in non-standard condition ................................................17  Climb and descent at different weight and altitude...............................................................30  AIRCRAFT SYSTEM EQUIPMENT................................................................................................1 Power plant ............................................................................................................................1 Fuel System .........................................................................................................................21 Oil system ............................................................................................................................34 Hydraulic system..................................................................................................................38 Fire-extinguish and neutral gas system................................................................................56 Air-conditioning system ........................................................................................................61 Anti-icing heating system .....................................................................................................71 General ................................................................................................................................71 Oxygen system ....................................................................................................................79 Flight control system..............................................................................................................84 Communication System .....................................................................................................247 Radar system.....................................................................................................................282 Instrument system..............................................................................................................320 Starting power and onboard power equipment...................................................................369
  20. 20. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOC 3/(4 Blank) June 30, 2012 SUBJECT PAGE Signal, Illuminating apparatus.............................................................................................380 Sighting, airdlift, airdrop and parachuting equipment..........................................................385 Electric signal gun deviceXQ-1A ........................................................................................392 APPENDIX A ............................................................................................................................... A1 APPENDIX B COMMON KNOWLEDGE INTRODUCTION ...................................................... B1 APPENDIX C FEATURES OF VARIOUS CLOUDS AND THEIR CORRESPONDING FLIGHT CONDITIONS........................................................................................C1 APPENDIX D AIRCRAFT ICE ACCRETION INTENSITY GRADE............................................D1
  21. 21. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL TOC 4 June 30, 2012 THIS PAGE INTENTIONALLY LEFT BLANK
  22. 22. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-1 June 30, 2012 GENERAL INTRODUCTION Y8F200W is the multifunctional medium transport aircraft of mid range. It mainly serves the army as air transportation of cargo, arming equipment, armed soldiers, the wounded, parachuting soldiers and release of small and large-sized cargo and equipment. For the customization purpose, some adaptation, replacement and adjustment are conducted to the aircraft like replacement of partial avionics equipment and high-failure rate equipment, instrument panel distribution adjustment, cargo transportation system interchangeability and loading effective improvement, floor modification modification in cargo compartment, airframe surface repaint, addition of engine fuel auto shutoff function and ground auto-cleaning function, addition of interface between cockpit and air-conditioner ground vehicle, and adaptation of aircraft structure, ECS, oxygen system, living facilities, power distribution system and illumination system, etc. The crew members include pilot (Captain), copilot, navigator, communicator and mechanic. The aircraft is of metal semimonocoque construction with cantilever high-wing, single vertical tail and turnup at the fuselage aft. The fuselage section from frames 0~59 are of airtight cabin, of which, frames 0~8 are the cockpit and frames 9~43 are airtight cargo compartment. For loading convenience, the floor of cargo cabin has slope at its rear section. The fuselage aft turnup angle is 18o 43’, and two cargo cabin doors which are openable in the air are located at the large opening of frames 43~59, and frames 65~68 at the fuselage aft is the non-airtight equipment cabin. The tapered wing is of non-geometrical twist along wing span direction and is separated as center wing, outboard-inboard and outboard wing by two separation surfaces. Four WJ-6 engines are suspended at spar I of outboard-inboard wing, and the double-seam extension flaps are suspended behind spar II. The two differencial ailerons cooperating with interference board are suspended behind the spar II of outboard wing.
  23. 23. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-2 June 30, 2012 The tricycle landing gears are of retractable/extensible type, and the four-wheel bogie main landing gear at both sides of the fuselage is retractable inward to the belly. The doble-wheel nose landing gear which is retractable backward is at frame 9. The aircraft has 10 wheels, all of which are equipped with low-pressure tyres, enabling the aircraft to takeoff and land on strip, grassland, gravel and sand runway. The nose wheel is equipped with nose wheel steering turning mechanism linked with the rudder control mechanism, and the main wheel is equipped with hydraulic brake device. The hydraulic system is composed of two independent sub-systems at left and right side and standby hand pump and electrical pump system. The two sub-systems at both sides which are independent to each other are equipped with hydraulic reservoir, hydraulic pump and hydraulic accessories and two sub-systems can work independently for power plant operation or cooperatively as standby control mechanism. The two sub-systems are controlled by the communication valve. Pressurization of hydraulic tank is realized through the pressurized air from engine compressor, so that normal oil supply is guaranteed regardless of the flight status and altitude. Total volume of hydraulic system is 28.595gal (130L), with its operating pressure being 1705~2203psi (11.76~15.19 MPa) (120~155 kgf/cm2 ). The hand pump and electrical pump system aims to control operation of each part on ground and serves as standby system in the air in emergency. Flight control system of the aircraft consists of primary control system and auxiliary control system. The primary control system is of rigid pull rod control, and is equipped with the hydraulic control surface of KJ-6C autopilot, the control surface receives the control signal from autopilot. The aircraft can be controlled individually or cooperatively by pilot (Captain) and copilot through the primary control system. The airborne oxygen system and two sets of high-altitude facility can gurantee normal living and working conditions for the crew members. The high-altitude facility fulfills airtight cockpit pressurization, heating and cooling requirement of the aircraft, while the air is supplied from stage X compressor of the engine. The low-altitude ventilation system on the aircraft serves to ventilate the cabin during low-altitude flight. Pressure difference inside and outside the cabin is not more than 6.67psi (0.046 MPa) (0.469 kgf/cm2 ). The air-conditioner interface system inside the cockpit can connect with the air-conditioner vehicle on ground in short time to supply the conditioned air to the aircraft. The oxygen is supplied in form of gas and the max. storage is 21.996gal (100 L).
  24. 24. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-3 June 30, 2012 The aircraft is equipped with anti-icing device. Deicing of engine inlet duct at its leading edge, engine compressor inlet guide vanes assembly is realized through the hot air, while that of propeller blade, propeller cap and windshield glass is of electrical-driven. The WJ-6 turbine propeller engine, with its power of 3126kW (4250 equivalent horsepower) per set is installed on the wing through engine case and engine nacelle support frame. The engine is started by direct current and designed with auto/manual fuel shut-off, overheat protection and ground cleaning functions, and is controlled by the steel cable. The engine propeller is known as J17-G13 four-blade metal propeller and is equipped with auto feathering pitch control device. There are 26 rubber fuel tanks inside the left and right wings, and the outboard wing is equipped with the integrated fuel tank. The fuselage tank is inside the anti-stress fuel tank cabin under floor of fuselage frames 33~41. Fuel consumption of the fuel system is contolled automatically or manually as per certain sequence, and the fuel can be added by means of auto-pressure refuelling or manually from the filler. The fireproof equipment and effective fire extinguisher can detect and put out the fire timely. The neutral gas to fuel tank from the neutral-gas system forms the anti-explosive media above the fuel surface, enhancing safety of the fuel system. Moreover, during emergency landing process, the neutral gas inside the fuel tank can increase the fuel pressure on its surface, thus improving the reliability of the fuel supply system. Aircraft is equipped with 28VDC, single- phase 400Hz 115VAC and three-phase 400Hz 36VAC. Direct current power supply includes QF12-1 starter generator (8 sets) supplying 28VDC with rated output power of 12kW for each, QF-24 starter generator (1 set) supplying 28VDC with rated output power of 18kW and 20GNC28B battery (4 sets) supplying 24VDC. Alternatiing current (AC) power supply includes JF-12 AC generator (4 sets) and three-phase alternating current includes 2 sets of SL-1000E three-phase inverter. In addition, the aircraft is also equipped with a DIAJ-0603 static inverter, its input voltage is 28VDC and output voltage is 110VAC/60Hz with rated output power of 3 kVA.
  25. 25. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-4 June 30, 2012 The airborne navigation system mainly includes HG-593Y8 laser strapdown inertial/satellite combination navigation system, 2101 I/O GPS navigation system, HZX-1M altitude heading reference system(AHRS), XAS-3M air data system and WL-11 ADF, JD-3A TACAN, KRA405B radio altimeter, VOR-432 VOR/ILS, KDM 706A DME distance measuring equipment and MK VIII enhanced ground proximity warning system. The navigation system integrated by these devices is cross-linked with KJ-6C autopilot to control the flight automatically. The communication system consists of TKR-200A2 HF radio, the TKR123E-III VHF radio, and JT-Y8F200W intercom with AIRMAN 750 headset. In addition, the aircraft is equipped with JYL-6AT meteorological radar, TCAS-94 airtraffic alarming and anti-collision system, and JZ/YD-126E IFF transponder. The airborne instrument mainly includes BK-43 airspeed indicator, BG-1A barometric altimeter, BC-10 elevation speedometer, BUC-26D capacitance-type fuel gauge, FJ-30D6 flight data recorder and XFJ-12B cockpit audio frequency recorder, etc. The aircraft can be equipped with airdrop side guide rail, cargo transportation guide rail, stop lock, rollway, mooring ring, seat and stretcher etc. to fulfill multi-purpose requirement. Air transportation equipment on the aircraft mainly include electric winch, beam crane, cargo transportation side guide rail, stop lock, cargo transportation rollway, mooring ring, capative cable, tie-down net and stop force component pad, etc. Airborne extraction equipment mainly consists of airdrop side guide rail, airdrop rollway, extraction parachute releasing device, extraction sighting equipment, electrical parachute rope recovery mechanism, airdrop and airborne signal device and airdrop electrical control device, etc. The aircraft can also be equipped with 86 seats for armed soldier or airborne parachute soldiers; it can also be equipped with 72 sets of rescue stretchers for rescuing the seriously injured personnel during the air transportation process.
  26. 26. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-5 June 30, 2012 AIRCRAFT TECHNICAL DATA Principal geometrical data General data (a) Overall length 111.62ft (34.022m) (b) Overall height LG free 36.61 ft (11.160m) LG compressed 35.20 ft (10.730m) (c) Min. suspension height of belly to ground upon landing gear compression 2.04 ft (0.622m) (d) Suspension height of cargo cabin floor at frame 43 4.47 ft (1.361m) (e) AOA of parking aircraft 5o 15’ (f) Max. width of fuselage (with laning gear bay) 14.88 ft (4.536m) (g) Max. height of fuselage 14.44 ft (4.40m) (h) Column diameter of fuselage (frames 17-33) 13.45 ft (4.10m) (i) Interior dimensions of fuselage cargo cabin Volume 4859.30ft3 (137.60m3 ) Length 48.23 ft (14.7m) Width (along floor surface) Frames 9~13 9.84 ft ~11.48 ft (3.000m~3.500m) Frames 13~25 and frame 30~43 11.48 ft (3.500m) Frames 25~30 9.84 ft (3.000m) (j) Height of cargo cabin Frames 9~14 7.38 ft ~8.2 ft (2.25m~2.50m) Frames 14~25 8.2 ft (2.50m) Frames 25~30 7.87 ft (2.40m) Frames 30~31 7.87 ft ~8.53 ft (2.4m~2.6m) Frames 31~43 8.53 ft (2.60m)
  27. 27. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-6 June 30, 2012 (k) Boarding gate dimension Height × width 4.77 ft × 2.62 ft (1.455m × 0.8m) Wings (a) Wing span (along chord plane) 124.67 ft (38m) (b) Area (including area covered by fuselage) 1311.689 ft2 (121.86m2 ) (c) Mean aerodynamic chord 11.322 ft (3.451m) (d) Aspect ratio 11.85 (e) Wing sweep angle at 25% chord 6o 50’34’’ (f) Wing dihedral angle Center wing 0o Outboard-inboard wing (relative to center wing) 1o Outboard wing (relative to inboard wing) -3o (g) Wing incidence 4o (h) Length of single aileron 18.98 ft (5.784m) (i) Aileron area 84.389 ft2 (7.840m2 ) (j) Maximum deflection angle of aileron Upwards (25±1)o Downwards (15+2 -1 )o (k) Aileron trim tab area 9.042 ft2 (0.84m2 ) (l) Max. deflection angle Upwards (6±1)o Downwards (6±1)o (m) Max. turning angle when the aileron turns to Max. limit position 135o (n) Flap area 289.657 ft2 (26.910m2 ) (o) Length of single flap 35.958 ft (10.960m)
  28. 28. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-7 June 30, 2012 (p) Flap deflection angle Takeoff 15o ~(25±1)o Landing (35±1)o (q) Flap Double-slot zap type (r) Length of spoiler (at half wing) 3.609 ft (1.100m) (s) Height of spoiler at full extension (aileron upwards to 25o ) is 5.51 in±0.20in (140±5mm) (spoiler tends to protrude when aileron deflects to 3o ) Tail (a) Area of horizontal tail 291.164 ft2 (27.050m2 ) (b) Stabilizer area of horizontal tail 214.729 ft2 (19.949m2 ) (c) Span of horizontal tail 40.013 ft (12.196m) (d) Mean aerodynamic chord of horizontal tail 7.851 ft (2.393m) (e) Dihedral angle of horizontal tail 0o (f) Incidence angle of horizontal tail (relative to wing chord) -4o (g) Elevator area 76.434 ft2 (7.101m2 ) (h) Max. deflection angle of rudder Upwards 28o ±1o Downwards 15o ±1o (i) Elevator trim tab area 8.374 ft2 (0.778m2 ) (j) Max. deflection angle of rudder trim tab (upon steel cable control) at up and down position 12o ±1o (k) Area of vertical fin (from upper fuselage, excluding dorsal fin) 21.503m2 (l) Stabilizer area of vertical fin 161.093ft2 (14.966m2 ) (m) Vertical tail span 19.13 (5.83m) (n) Mean aerodynamic chord of vertical tail 13.28 (4.048m) (o) Rudder area 70.364ft2 (6.537m2 ) (p) Max. deflection angle of rudder Leftward and rightward 25o ±1o (q) Rudder trim tab area 4.123ft2 (0.383m2 ) (r) Rudder spring force servo tab area 4.726 ft2 (0.439m2 )
  29. 29. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-8 June 30, 2012 (s) Max. deflection angle of rudder trim tab Leftward and rightward 18.5o ±1o (t) Max. deflection angle of rudder spring force servo tab Leftward and rightward 13.5o ±1o Landing gear (a) Wheel track along the main wheel contour 17.756 ft (5.412m) Along the main wheel buffer strut 16.142 ft (4.920m) Wheel base 31.42 ft (9.576m) (b) Min. turning radius on ground 45.11 ft (13.75m) (c) Max. turning angle of nose wheel Manual control angle Leftward and rightward 35o Rudder control angle Leftward and rightward 8o ±2o (d) Favorable taxiing speed of the aircraft when turning with nose wheel handle 2.70kn~3.24kn (5~6km/h) (e) Main wheel dimension 41.339 in×11.811 in (1050mm×300mm) (f) Nose wheel dimension 35.433 in×11.811 in (900mm×300mm) (g) Air pressure of tyre Within the range of normal takeoff: Main wheel (85.57+7.25 0 )psi ((0.59+0.05 0 ) MPa) Nose wheel (71.07+2.90 -1.45 )psi ((0.49+0.02 -0.01 )MPa) At max. takeoff weight (61t) Main wheel (100.08+7.25 0 )psi ((0.69+0.05 0 )MPa) Nose wheel 73.97psi (0.51MPa) (h) Braking clearance 0.059in~0.138in (1.5mm~3.5mm) (i) Exposive buffer strut (upon parking and compression) Within the range of normal takeoff: Nose buffer strut 3.937in~9.449in (100~240mm) Main buffer strut 1.693in~4.528in (43~115mm) At max. takeoff weight (61t) Nose buffer strut 1.693in~4.528in (70~200mm)
  30. 30. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-9 June 30, 2012 (j) Parking compression of aircraft tyre Parking compression of aircraft tyre for main landing gear wheel 2.953in~3.543in (75~90mm) Parking compression of aircraft tyre for nose landing gear wheel 1.378in~1.987in (35~50mm) Power plant and trubo power starter generator WJ-6 Engine data (a) Dimension Length 122 in±0.079 in (3099mm±2mm) (with bullet 140 in±0.197 in (3558mm±5mm)) Width 35.118in±0.039 in (892mm±1mm) Height 46 in±0.0118 in (1174mm±1mm) (b) Net weight (with accessories) 1200kg+2% (c) Engine rotating speed Operating speed (12300+90 )r/min(95.5%~96.2%) Idle on ground (10400+200 -50 )r/min(80.5%~82.5%) Cold running speed (30s) 17%~22% (d) Engine acceleration From idling on ground to takeoff Not exceed 20s From idling in the air to takeoff Not exceed 10s (e) Engine deceleration 8s~10s (f) Relative incidence angle between engine and wing -4o (g) Shut off speed of air compressor air-bleed valve 5th stage (11340+130 ) r/min (88%~89%) 8th stage (9340+200 ) r/min (72.5%~74%) (h) Pressure ratio of air compressor (Maximum continuous power condition H= 26247ft (8000m), V= 574.15ft/s (175m/s) 9.2 (i) Airflow ((Maximum continuous power condition H=0, V=0) 20.5kg/s
  31. 31. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-10 June 30, 2012 (j) Engine data in different operating conditions is shown in Table 1-1. Table 1-1 Engine data in different operating conditions (H=0, V=0, PH=101.3kPa, tH=15o C) Service condition Throttle angle Equivalent power rate (kW) Axis power rate (kW) Fuel consumption (kg/h) Takeoff 98o ~105o 3126 2868 1030 Max. continuous power condition 84±2o 2567 2331 927 0.85 Max. continuous power condition 72±2o 2184 1971 842 0.7 Max. continuous power condition 60±2o 1846 1589 757 0.6 Max. continuous power condition 52±2o 1525 1341 701 0.4 Max. continuous power condition 35±2o 961 805 578 0.2 Max. continuous power condition 20±2o Idling on ground 0o Propeller data (a) Model J17-G13 (b) Number of blade 4 (c) Diameter of blade 14.76ft (4.5m) (d) Rotating direction (Along the flight direction) Anti-clockwise (e) Blade incidence(R=5.25ft (1.6m) at the section) Min. blade angle (starting angle) 0o Mid-range limiting angle 12o Feathering angle 83o 30’ Ground hydraulic feathering angle 40o ~46o (f) Blade angle variation 0o ~83o 30’ (g) Propeller operating speed 1075r/min
  32. 32. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-11 June 30, 2012 (h) Full feathering position time Engine operative Not exceed 10s Engine shutdown Not exceed 20s (i) Unfeather time In the air Not exceed 10s On ground Not exceed 25s (j) Rotating inertia 2.382kg•m•s2 (k) Net weight (without hub fairing component and current collector) 408kg+2% (l) Area of propeller airflow passing the wing 53% (m) Clearance between propeller and the fuselage 2.17ft (0.66m) (n) Suspension height of blade tip to ground Inboard engine 6.34ft (1.932m) Outboard engine 6.51ft (1.985m) (o) Propeller pulling arm on horizontal surface Inboard engine 15.59ft (4.715m) Outboard engine 31.28ft (9.533m) Caution Upon feathering ground test, oil temperature is required to be above 25o C.
  33. 33. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-12 June 30, 2012 Turbo starter generator (a) Power rate (at the terminal of QF-24 power generator) 56kW~60kW (b) Output axis power rate 70kW~73.5kW (c) Net weight 170kg (Not exceed 190+5 kg for trubo starter generator with turbo protection device). (d) Operational altitude 0ft~13780ft (0m~4200m) (e) Contour dimension Length (to the end of short exhaust pipe) 62.20in±0.31in (1580mm±8mm) Height Not exceed 26.38in (670mm) Width 22.64in (575mm) (f) Total operating hour of turbo starter generator should not exceed 172h (total engine start hour is 72h, total hour of power supply to airborne network is 100h, and total start frequency per engine is 2000 times).
  34. 34. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-13/(14 Blank) June 30, 2012 AIRCRAFT THREE-VIEW ARRANGEMENT For details, see Figure 1-1. 14.83 4520 12.6 (3840) 111.62 (34022) 31.42 (9576) 26.61~35.3 (11160~10760) 124.67 (38000) 16.14 (4920) 40 (12196) Figure 1-1 Three-view arrangement of the aircraft
  35. 35. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION I GENERAL 1-14 June 30, 2012 THIS PAGE INTENTIONALLY LEFT BLANK
  36. 36. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-1 June 30, 2012 OPERATIONAL LIMITATION GENERAL OF FLIGHT LIMITATION Minimum crewmembers: Minimum crewmembers: five persons, i.e., pilot (captain), co-pilot, navigator, communicator and flight engineer. Service range: (a) Day and night flight (b) Instrument landing (c) Icing condition of mid-level or below FLIGHT LIMITATION (a) Maximum banks are not more than 30o , and under complicated weather conditions not more than 15o during banking and turning. (b) Maximum angle of attack of wing is 12o 30’ during take-off and landing. (c) The allowable 90o crosswind speed during normal take-off and landing is not more than 39.37ft/s (12m/s), and the experienced pilot is allowed to take off and land 90o crosswind within the speed of 49.21 ft/s (15m/s). (d) Go-around altitude of the aircraft is usually not less than 164ft (50m). Under special circumstances go-around at any altitude is allowed, as long as the four engines are all in operation and their throttle levers are all over 16o . (e) The door is not allowed to open upon aircraft takoff; in case that the door can not be closed due to its control system failure, normal landing is permitted with AOA of the wing ≯9o (fuselage AOA≯5o ) (f) Pressure difference inside and outside of pressurized cabin is not more than 6.67psi (0.046MPa).
  37. 37. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-2 June 30, 2012 SPEED LIMITATIONS (a) Speed limitation (Vmax) for level-flight with different air-borne weight and altitude is in Table 2-1. Table 2-1a Speed limitation for level flight Air-borne weight (t) Altitude (ft) IAS (kn) <55 <18045 Vmax≯281 >18045 M≯0.6 ≥55 <23950 Vmax≯248 >23950 M≯0.6 Table 2-1b Level speed limitation Air-borne weight (t) Altitude (m) Equivalent speed (km/h) <55 <5500 Vmax≯520 >5500 M≯0.6 ≥55 <7300 Vjx≯460 >7300 M≯0.6 (b) Speed limitation (Vjx) for gliding with different airborne weight and altitude and short-period flight is in Table 2-2. Table 2-2a Gliding speed limitation Airborne weight (t) Altitude (ft) IAS (km/h) <55 <17388 Vjx≯329 >17388 M≯0.7 ≥55 <21325 Vjx≯302 >21325 M≯0.7 Table 2-2b Gliding speed limitation Airborne weight (t) Altitude (m) IAS (km/h) <55 <5300 Vjx≯610 >5300 M≯0.7 ≥55 <6500 Vjx≯560 >6500 M≯0.7
  38. 38. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-3 June 30, 2012 (c) Speed limitation polar curve as per Table 2-1 and Table 2-2 is shown in Figure 2-1. H(ft) V b (kn) Longperiodflight Shortperiodflightandgliding V max V jx M=0.6 M=0.7H=23950ft H=18045ft H=21325ft H=17388ft 227 238 248 252 270 281 292 302 313 324 335 346 356 367 26247 22966 19685 16404 13123 9843 6562 3281 0 Figure 2-1a Speed limitation polar curve 420 440 460 480 500 520 540 560 580 600 620 640 660 680 0 1000 2000 3000 4000 5000 6000 7000 8000 H(m) Vb(km/h) Longperiodfight Shortperiodflightandgliding Vmax Vjx M=0.6 M=0.7H=7300 H=5500 H=6500 H=5300 Figure 2-1b Speed limitation polar curve
  39. 39. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-4 June 30, 2012 (d) Speed and Mach number limit for emergency landing is the same with that in Table. Load limit and descending rate for emergency landing recovery should not exceed 1.5g and 131ft/s (40m/s) respectively. (e) IAS should be no more than 189 kn (350km/h) when the cargo cabin is at open position. (f) IAS of airdrop and airborne is 173kn~189kn (320km/h~350km/h) and 157kn~189kn (290km/h~320km/h) respectively. (g) Upon landing gear retraction/extension, readout of flight speed Vmeter should not exceed 189 kn (350km/h). (h) Flap extension IAS: (i) When flap is down by 25o , IAS should not exceed 184kn (340km/h), and when it is down by 35o , the readout should be no more than 162kn (300km/h). (j) When the aircraft is taxiing on ground at the speed of 2.7kn~32.4kn (5km/h~60km/h), or 81kn (150km/h) under special condition, operation of nose wheel steering handle is allowed. However, gentle operation is required for the latter situation. (k) In vertical blast region, lower flight speed timely in case of G-load caused by the gust. 1) In case of the strongest blast (equivalent wind speed: 65.6ft/s (20m/s)), lower the flight speed as Vzj (See Table 2-3). Table 2-3a Lowering speed under gust Altitude (ft) 0 6562 13123 19685 Vzj (kn) 180 182 186 192 Table 2-3b Lowering speed under gust Altitude (m) 0 2000 4000 6000 Vzj (km/h) 333 337 344 355 2) Under equivalent wind speed of 49.2 ft/s (15m/s), flight speed should not exceed that of max. level flight (Vmax). See Table 2-1. 3) Under equivalent wind speed of 26.2 ft/s (8m/s), flight speed should not exceed that of dive limit (Vjx). See Table 2-2. Note In case of gust, flight speed should be within the tolerance of Max. gust speed as per designation.
  40. 40. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-5 June 30, 2012 (l) Max. maneuver speed of level flight with different airborne weight, altitude, flap & landing gear up is in Table 2-4. Table 2-4a Maneuver speed (IAS) Altitude(m) Airborne weight (t) <19685 ≥19685 ≤54 151 162 >54 173 184 Table 2-4b Maneuver speed (IAS) Altitude(m) Airborne weight (t) <6000 ≥6000 ≤54 280 300 >54 320 340 (m) Upon landing light down, flight speed should not eceed 162 kn (300km/h). (n) Min. allowable speed and falling spiral speed is in Table 2-5. Table 2-5b Min. allowable speed and falling spiral speed Altitude (ft) Landing gear status Flap angle Airborne weight (t) Min. allowable speed (kn) Falling spiral speed (kn) Remark 15748~18045 UP 0o 48.7 140 121 1. Throttle angle 20o 2. IAS speed DOWN 25o 48.4 115 103 DOWN 35o 48.2 109 97 Table 2-5b Min. allowable speed and falling spiral speed Altitude (m) Landing gear status Flap angle Airborne weight (t) Min. allowable speed (km/h) Falling spiral speed (km/h) Remark 4800~5500 UP 0o 48.7 260 225 1. Throttle angle 20o 2. IAS speed DOWN 25o 48.4 213 190 DOWN 35o 48.2 202 179 (o) Figure 2-2 shows the flight envelope when all engines are operated with the airborne weight of 49t.
  41. 41. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-6 June 30, 2012 H(ft) 3281 24606 16404 8202 108 216 324 432 V(kn) Vmin Vks Vmax(Max.continuouspowercondition) Vmax(Max.) Max.speedpressurelimitfor levelflightq=12740Pa Max.glidingspeed pressureq=17640Pa 0.7Max.continuous powercondition Figure 2-2a Flight envelope of four operated engines H(m) 10000 7500 5000 2500 200 400 600 800 V(km/h) Vmin Vks Vmax(Max.continuouspowercondition) Vmax(Max.) Max.speedpressurelimitfor levelflightq=12740Pa Max.glidingspeed pressureq=17640Pa 0.7Max.continuous powercondition Figure 2-2b Flight envelope of four operated engines
  42. 42. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-7 June 30, 2012 WEIGHT AND C.G. LIMITATIONS Basic data Maximum take-off weight 61t Normal takeoff weight 56t Normal landing weight 52t Theriotical empty weight 35.20t (See MRB for empty weight per aircraft) (Specific weight of fuel 0.775kg/L) Max. fuel quantity of wing tank 15.020t Max. fuel quantity of fuselage tank (Specific weight of fuel 0.775kg/L) 2.200t Dead fuel 395kg Fixed weight 778kg Theoretical C.G of empty aircraft 25.01%CA (See MRB for C.G per empty aircraft) Normal range of C.G 22%CA~28%CA Optimum range of C.G 25%CA~28%CA Weight and C.G. limitations Weight limitations Maximum take-off weight 61t Maximum taxiing weight 61.5t Maximum landing weight 58t Allowable C.G With aircraft weight equal to or less than 56000kg 16%CA~32%CA With aircraft weight greater than 56000kg 18%CA~32%CA
  43. 43. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-8 June 30, 2012 Fuel quantity limitation for typical airdrop and air transportatoin Upon airdrop of cargo for 12 sets of 1m loading platforms, total fuel quantity of the aircraft should be not less than 4000kg (with dead fuel of 395kg). Upon airdrop of cargo for 6m loading platform (weight: 7400kg) and 4m loading platform (weight: 5800kg), total fuel quantity of the aircraft should be not less than 4000kg (with dead fuel of 395kg). Total fuel quantity should be not less than 2600kg (with dead fuel of 395kg) when the aircraft is fulfilled with the wounded. Fuel consumption influence towards C.G Variation of C.G as per fuel consumption in different conditions is shown from Figure 2-3 to Figure 2-11. 60000 55000 50000 45000 40000 35000 10 15 20 25 30 35 RelativeC.Goftheaircraft(%CA ) C.G backward limit C.G forward limit Weight of the aircraft (kg) Note Aircraft takeoff weight is 53459kg, and fuel quantity is 17220kg. Figure 2-3 Variation of C.G as per fuel consumption in empty ferry flight
  44. 44. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-9 June 30, 2012 RelativeC.Goftheaircraft(%CA ) C.G backward limit C.G forward limit Weight of the aircraft (kg) 60000 55000 50000 45000 40000 35000 10 15 20 25 30 35 Note a) Aircraft takeoff weight is 61000kg, fuel quantity is 14210kg, and bulk cargo weight is 10000kg. Figure 2-4 Typical variation of C.G. for typical transportation of containerized cargo RelativeC.Goftheaircraft(%CA ) C.G backward limit C.G forward limit Weight of the aircraft (kg) 60000 55000 50000 45000 40000 35000 10 15 20 25 30 35 Note Aircraft takeoff weight is 61000kg, fuel quantity is 15211kg, and 3 pieces of pallet (96’’×125), total weight is 9000kg. Figure 2-5 Variation of C.G as per fuel consumption for typical transportation of containerized cargo
  45. 45. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-10 June 30, 2012 RelativeC.Goftheaircraft(%CA ) C.G backward limit C.G forward limit Weight of the aircraft (kg) 60000 55000 50000 45000 40000 10 15 20 25 30 35 Note Aircraft takeoff weight is 61000kg, fuel weight is 14178kg, and total weight of 86 armed soldiers is 10320kg. Figure 2-6 Variation of C.G as per fuel consumption for armed soldier transportation RelativeC.Goftheaircraft(%CA) C.G backward limit C.G forward limit Weight of the aircraft (kg) 60000 55000 50000 45000 40000 10 15 20 25 30 35 Note Aircraft takeoff weight is 60961kg, fuel weight is 17220kg, and total weight of 60 paratroopers is 9000kg. Figure 2-7 Variation of C.G as per fuel consumption for airborne paratrooper transportation
  46. 46. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-11 June 30, 2012 RelativeC.Goftheaircraft(%CA) C.G backward limit C.G forward limit Weight of the aircraft (kg) 60000 55000 50000 45000 40000 10 15 20 25 30 35 Note a) Aircraft takeoff weight is 60903kg, fuel quantity is 17220kg, 3 medical care personnel, 72 seriously wounded persons and 17 walking injuries and total weight is 6675kg. b) Residual fuel in the tank should be not less than 2600kg during flight. Figure 2-8 Variation of C.G as per fuel consumption for the wounded transportation
  47. 47. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-12 June 30, 2012 60000 55000 50000 45000 40000 35000 15 20 25 30 C B C A B A’ ’ ’ RelativeC.Goftheaircraft(%CA ) Weight of the aircraft (kg) C.G forward limit C.G backward limit Note a) Curve AA indicates variation of C.G as per fuel consumption with the weight of empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 12 sets of 1m loading platform(loading status) + full fuel of fuselage tank and wing tank (variation is 20.7 %CA~28.2 %CA). b) Curve BB indicates variation of C.G as per fuel consumption with the weight of empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 12 sets of 1m loading platform(unloading status) + full fuel of fuselage tank and wing tank (variation is 21.0 %CA~29.3%CA). c) Curve CC indicates variation of C.G as per fuel consumption with the weight of empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 12 sets of 1m loading platform(loading platform I-VI in unloading status and VII-XII in loading status) + full fuel of fuselage tank and wing tank. Upon airdrop, residual fuel in the tank should not be less than 4000kg. Figure 2-9 Variation of C.G as per fuel consumption for 12 sets of 1m loading platform in airdrop status
  48. 48. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-13 June 30, 2012 60000 55000 50000 45000 40000 35000 15 20 25 30 c C B A B A RelativeC.Goftheaircraft(%CA ) Weight of the aircraft (kg) C.G forward limit C.G backward limit ’ ’ ’ Note a) Curve AA’ indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 4500kg loading platform + 4500kg loading platform + 14742kg of fuel) in takeoff status (variation is 29.3 %CA~ 31.0%CA). b) Curve BB’ indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 4500kg loading platform (No.1) +4500kg loading platform (No.2) + 14742kg of fuel in takeoff status (variation is 21.0 %CA~24.7 %CA) when both loading platforms (No.1 and No.2) are in unloading condition. c) Curve CC’ indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 4500kg loading platform(No.1) + 4500kg loading platform(No.2) + 14742kg of fuel) in takeoff status (variation is 29.3 %CA~ 31.0%CA) when loading platform(No.1) is unloaded and loading platform (No.2) is in loading condition (variation is 16.9 %CA~21.1%CA). Figure 2-10 Variation of C.G as per fuel consumption for 2 sets of 4m loading platform in airdrop status
  49. 49. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-14 June 30, 2012 60000 55000 50000 45000 40000 35000 15 20 25 30 c C B A B A Weight of the aircraft (kg) C.G forward limit C.G backward limit RelativeC.Goftheaircraft(%CA ) ’ ’ ’ Note a) Curve AA indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 7400kg loading platform +5800kg loading platform + 10542kg of fuel) in takeoff status (variation is 29.5 %CA~ 30.2 %CA). b) Curve BB indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 7400kg loading platform(No.1) + 5800kg loading platform(No.2) + 10542kg of fuel) in takeoff status (variation is 21.0 %CA~23.2 %CA) when both loading platforms(No.1 and No.2) are in unloading condition. c) Curve CC indicates variation of C.G as per fuel consumption with total weight of 61000kg (i.e. empty aircraft + fixed weight + basic configurated application item + configurated application item of airdrop loading platform + 7400kg loading platform(No.1) +5800kg loading platform(No.2) + 10542kg of fuel) in takeoff status when loading platform(No.1)is unloaded and loading platform(No.2)is in loading condition. Upon airdrop, residual fuel in the tank should not be less than 4000kg. Figure 2-11 Variation of C.G as per fuel consumption for 2 sets of 4m loading platform in airdrop status
  50. 50. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-15 June 30, 2012 G-LOAD LIMITATION (a) Upon takeoff, G-load at C.G should not exceed 2g. (b) Upon landing, G-load at C.G should not exceed 2.5g. (c) See Table 2-6 for static-strength-based G-load limitation in flight. Table 2-6 Flight G-load Aircraft weight (t) Min. fuel quantity of wing (t) Max. limit load (g) Min. limit load (g) V≤VjX V≤Vmax Vmax<V<VjX 38 2 2.96 -1 0 53 7 2.5 -1 0 61 10 2.17 0 0 61 5 2.0 0 0 (d) Load limitation Cargo load should not exceed the following limits marked on the plate: Concentrated cargo 16t Bulk cargo 20t
  51. 51. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-16 June 30, 2012 LIMITATIONS OF POWER PLANT (a) Engine continuous operation duration Take-off power condition 15min Ground idling power condition 30min (b) Percent of engine operating time in its total life: Takeoff power condition 2.5% Maximum continuous power condition 32% See Table 2-7 for the maximum allowable turbine outlet gas temperature. Table 2-7 Maximum allowable turbine outlet gas temperature Engine service condition Engine operating status Allowable turbine exhaust temperature (o C) On ground Takeoff to≤15o C, 510 to>15o C, 560 Inflight Below 26247ft (8000m) Takeoff 510 Max. continuous power 475 Cruising power 450 Above 26247ft (8000m) Takeoff 540 Max. continuous power 495 Cruising power 470 Note The turbine outlet gas temperature in the Table is specified per standard atmosphere condition. When the difference between ambient temperature and the standard air temperature is ±1o C, the gas temperature varies ±1o C accordingly.
  52. 52. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-17 June 30, 2012 (c) Engine operational limitations 1) The maximum allowable turbine outlet gas temperature is 750oC upon engine start. 2) The maximum allowable speed for engine acceleration is 13260rpm. The maximum engine vibration overload factor K: Not exceed 2.5g for ex-factory period Not exceed 3.5g during operation. 3) See Table 2-8 for allowable bleed rate of compressor under all conditions. Table 2-8a Allowable bleed rate of compressor Frequent bleed rate (various power setting) Numbers of operating engines Four engines Three engines Two engines Altitude 32808ft 26247ft 16404ft Engine bleed rate ≯0.345kg/s ≯0.46kg/s ≯0.55kg/s Periodic bleed rate Maximum continuous power H=0, V=0, tH=15o C≯0.15kg/s H=26246ft, V=574 ft/s, tH=-30o C≯0.1kg/s Ejection cooling bleed rate On ground 0.4kg/s for small throttle setting 0.6kg/s for 0.2 Max. continuous power setting Total bleed rate Maximum continuous power H=0 V=0 tH=15o C Bleed rate does not exceed 0.495kg/s. H=26247ft Bleed rate does not exceed 0.46kg/s V=574 ft/s tH=-30o C Note a) Engine deicing system turning on is allowed only when the aircraft is likely to ice during take-off. b) Engine deicing system can be used under all working conditions on the ground. c) Periodic bleed rate means the bleed rate besides frequent bleed rate, such as wing deicing, etc.
  53. 53. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION II OPERATIONAL LIMITATION 2-18 June 30, 2012 Table 2-8b Allowable bleed rate of compressor Frequent bleed rate (various power setting) Numbers of operating engines Four engines Three engines Two engines Altitude 10000m 8000m 5000m Engine bleed rate ≯0.345kg/s ≯0.46kg/s ≯0.55kg/s Periodic bleed rate Maximum continuous power H=0, V=0, tH=15o C≯0.15kg/s H=8000m, V=175m/s, tH=-30o C≯0.1kg/s Ejection cooling bleed rate On ground 0.4kg/s for small throttle setting 0.6kg/s for 0.2 Max. continuous power setting Total bleed rate Maximum continuous power H=0 V=0 tH=15o C Bleed rate does not exceed 0.495kg/s. H=8000m Bleed rate does not exceed 0.46kg/s V=175m/s tH=-30o C Note a) Engine deicing system turning on is allowed only when the aircraft is likely to ice during take-off. b) Engine deicing system can be used under all working conditions on the ground. c) Periodic bleed rate means the bleed rate besides frequent bleed rate, such as wing deicing, etc. OPERATIONAL LIMITATION FOR AIR CONDITIONING SYSTEM (a) Air conditioning power on is not allowed when the aircraft is on ground or during take-off period. (b) Only one set of air conditioning system is allowed for leading edge deicing of the wing.
  54. 54. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-1 June 30, 2012 EMERGENCY PROCEDURES Various special events may occur during flight for different causes, such as mechanical failure, sudden weather change, operation mistakes and so on. Once any of such special cases occurs, it is necessary for the crewmember to judge accurately and rapidly so as to take action resolutely and effectively. ENGINE FAILURES If the engine or propeller fails in flight when automatic-feathering device is out of operation, there would be a quite large negative thrust that would make the aircraft controlling difficult. Therefore, if propeller of the shutdown engine does not feather automatically, the manual feathering shall be adopted in time. If the manual feathering fails, then the hydraulic emergency feathering should be used. The measures above can ensure feathering in common condition. In flight, only when all feathering systems fail simultaneously and the propeller rotates automatically, and flight speed is less than 227 kn~238 kn (420~440km/h), propeller stop can be released after windmilling speed is stablized. Symptoms of engine failure in flight (a) Aircraft banks and yaws to the side of faulty engine. (b) The red signal light for engine failure is on. (c) The pressure on torque indicator decreases. (d) The upstream fuel pressure of fuel nozzle and fuel instantaneous consumption drops sharply or pressure oscillating amplitude exceeds 42.64 psi (0.294MPa) (3kgf/cm2 ). (e) Turbine exhaust temperature increases or decreases. (f) Engine rotating speed increases or decreases and exceeds specified limitation, or rotating speed oscillates beyond ±2%. (g) Oil pressure decreases to 56.85 psi (0.392MPa) (4kgf/cm2 ) below. (h) The stop released signal light is on. (i) The reading of engine vibration indicator exceeds specified limitation. Warning light is on. (j) Oil in tank leaks out seriously. Once discovering the symptoms above, the aircrew should make decision correctly and adopt proper measures timely.
  55. 55. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-2 June 30, 2012 Engine failures during takeoff Once any engine shuts down during take-off running, the aircrew should work out solution as per current speed of the aircraft. If the speed is below decision speed, abort takeoff; or else takeoff should be continued. Operation procedures for aborting take-off (a) Keep the direction with the rudder, ailerons, nose wheels and brakes to prevent the aircraft from yawing abruptly and pull the four throttles back to 0o at the same time (pull the throttles at normal engine side back a bit quicker than that at the faulty engine side for correcting the aircraft yaw by throttle difference). (b) Push forward the control column for nose wheel extension to maintain the direction. (c) Release the stop for propellers of two symmetrical operating engines. (d) Lower flaps fully and slow down the aircraft by the brakes in time. If the runway is not long enough and the aircraft tends to fly out of the runway, decrease the speed with emergency brake. (e) When the running direction is no longer deviated and the aircraft speed is below 32.4 kn (60km/h), pull out the nose wheel steering handle, release propeller stop of the engine which is symmetrical to the shutdown engine. (f) If the running direction cannot be maintained after aborting take-off, the captain should pull out the nose wheel steering handle at the speed of less than or equal to 150km/h, to maintain the direction. Operation procedures for continuing take-off (a) The takeoff can be continued when aircraft running speed exceeds decision speed and that the malfunctioned engine feathering is already completed. At this moment, apply the rudder and push the helm towards the normal engine to maintain the direction, and the unstick speed should be 5.4kn~8.1kn (10km/h~15km/h) higher than normal in case of any deviation. (b) If engine failure occurs after aircraft unsticking, apply the rudder and push the helm towards the normal engine side rapidly and timely to maintain aircraft attitude.
  56. 56. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-3 June 30, 2012 (c) Judge propeller feathering status of the faulty engine as per the load of control mechanism and judgment of the flight engineer or pilot. If automatic feathering system fails, press the manual-feathering button rapidly for feathering. (d) Gear up with a speed of 135kn~140kn (250~260km/h) and an altitude not less than 16.4ft (5m), and climb with increasing speed, the climb gradient should not be less than 0.5%. (e) Retract the flaps step by step and reduce the load on the control column and rudder with trim tab when the altitude is not less than 328ft (100m) and aircraft speed is 162kn~167 (300~310km/h). (f) Pull the throttle of operating engine back to maximum continuous power condition (84o ). (g) Pull the throttle of shutdown engine back to 0o , set the shutdown switch to SHUTDOWN and put anti-fire switch at OFF position. (h) Climb to traffic pattern altitude, establish normal pattern and then make visual landing. Engine failures in flight (a) Operation procedures with the automatic feathering system being out of operation in flight 1) Maintain the aircraft attitude by applying the rudder and pushing the helm towards normal engine side to prevent the aircraft from banking and yawing. 2) Advance the throttles of operating engines to above 84o and maintain the specified flight attitude. 3) Judge the malfunctioned engine. 4) Following the captain’s command, the mechanic conducts feathering to the faulty engine (by pushing down manual feathering button or through emergency hydraulic feathering device). 5) Balance the aircraft with trim tabs to reduce the load on control column and rudder. 6) Retard the throttle of faulty engine back to 0o and retard the throttle of symmetrical engine to 40o ~60o . 7) Set the engine shutdown switch to SHUTDOWN position and put anti-fire switch at OFF position. 8) Manually extinguish fire of the faulty engine as per the actual situation.
  57. 57. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-4 June 30, 2012 (b) After any one of the four engines is inoperative in flight, the torque on the aircraft can easily be maintained by feathering the faulty engine in time and applying rudder and helm, the load on the rudder and stick can be eliminated completely by using trim tabs,so flight with three engines is not complicated. After one engine is feathered, the aircraft still possesses better stability and controllability and has enough excess thrust to climb, and climb to flight altitude of 26575ft (8100m) with take off weight of 51t. (c) Cautions 1) After engine fails, when automatically feathering with negative thrust, the throttle must be above 40o . 2) If the automatic feathering system fails and the indicated air speed is more than 189 kn (350km/h), the aircraft may buffet. In this case, the speed should be slowed down to below 189 kn (350km/h) first, and then conduct manual feathering. Operation features of landing with three engines operative (a) Set the trim tab to neutral position during final gliding. (b) When aircraft flies over the inner locator, set the throttle of the normal engine symmetrical to the faulty engine to the small throttle position as per the load and atmospheric temperature, and keep the gliding speed and correct the flight path of approach with the throttles of the symmetrical normal engines. (c) During floating, set the throttles of the two normal engines which are in symmetrical operation gently to 0o . Meanwhile, be sure to keep the direction, and prevent the aircraft from floating with side sliding. (d) After the aircraft touches down and keeps a stable running direction, release the stop of the propellers of the two symmetrical normal engines, and then pull the throttle of the normal engine symmetrical to the faulty engine back to 0o . At the latter stage of running when the aircraft speed is 32.4kn (60km/h), pull out the nose wheel steering handle to release the stop of the normal engine propeller symmetrical to the faulty one. (e) At the early stage of run, keep the direction with rudder and prevent the aircraft from yawing and banking with brakes and aileron if necessary. At the latter stage of run, keep the direction with the nose wheel steering handle. (f) The altitude for go around with three operative engines should not be below 164ft (50m), its operation procedure for missed approach is the same as that with four operative engines.
  58. 58. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-5 June 30, 2012 Air start of the engine (a) Only when the engines are completely normal (engine shutdown due to control error or other reasons and performance of special air start training), and that the pilot and the flight engineer have been specially trained for air starting, the air start may be allowed (start of the malfunctioned engine is not allowed in any case). (b) Engine air start envelop: The altitude between 6562ft~26247ft (2000~8000m); the indicated air speed within 162 kn~178 kn (300~330km/h). (c) Press of the START button on the panel is strictly forbidden when starting the engine in flight. The pilot and the flight engineer must coordinate for engine start. (d) Pre-start-up check 1) Set the throttle at 0o 2) Turn on the anti-fire switch (green signal light ON). 3) Check: the AIR-GROUND start changeover switch should be at AIR position. 4) Be sure the propeller stop switch should be at STOP position. 5) Put the engine shutdown switch at ON position. (e) Air start procedure 1) Remove the lead seal on protection cover of the air start switch 1-2s before propeller reversing, and put the switch at air start position (the sound of booster coil can be heard from the intercom). 2) Press the manual feathering button for propeller reversing until the engine speed reaches 15%~20%. In case that the engine speed grows slowly, press the button continuously until the speed indicates 22%~25%. At this moment, release the button and check that the fuel pressure in front of the nozzle should be 99.5psi~142psi (0.686MPa~0.98MPa) (7kgf/cm2 ~10kgf/cm2 ) and the fuel in combustion chamber for ignition (turbine exhaust temperature rise).
  59. 59. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-6 June 30, 2012 3) When turbine exhaust temperature reaches 300o C, turn off the air start switch and the engine will reach operating speed automatically. During propeller reversing process, in case that the fuel in combustion chamber does not ignite and the fuel temperature has no readout at the engine speed of 15%~20%, it is necessary to press the feathering button immediately and and turn off the engine shutdown and air start switches. 4) After the engine is at the normal rotating speed (95.5~96.2%), advance the throttle gently to 20o . Check the operating condition of engine as per the indicator readout, and then advance the throttles to flight requirement position. 5) During the air start, a yawing moment will occur toward the starting engine side for the propeller reversing moment, and the aircraft would yaw discontinuously toward the contrary side with engine speed increase. In this case, apply the helm and the rudder to overcome the yawing. (f) Cautions for air start 1) During engine start, if the air start change-over switch is not turned off timely, the start may be failed and propeller will autorotate, generating heavy negative thrust. 2) If the air start change-over switch is misconnected to the operating engine after air start is completed, then: a) The operating engine will fether automatically (operating status must be above 0.7 Max. continuous power). b) Autofeathering is not allowed when engine throttle angle is below 40o since the engine will be in wind-milling status or its operating status will not be stable. 3) One engine is not allowed to start for more than three times for a single training, or else the ignitor might be damaged. 4) Restart interval is 2-3min 5) Ignitor ground check is required after engine air start. 6) Feathering pump can not work normally when oil temperature is below 20o C thus air start is not allowed. 7) When flying in icing condition, air start is not allowed until the engine inlet is deiced.
  60. 60. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-7 June 30, 2012 (g) Two engines fail at the same side 1) When two engines fail in a condition above 0.7 maximum continuous power (throttles at 62o ), the propeller will automatically feather within 2~3s. If engines fail when throttles are below 40o ±2o , the propeller will not feather automatically, thus manual feathering button must be used. 2) In the flight with two engines failed on the same side (the failed engines have been feathered), the aircraft posses enough thrust to ensure the aircraft to keep a level flight and climb (the aircraft can ascend to an altitude of 15584ft (4750m) with takeoff weight of 47t) and has controllability and stability for turning left or right and approaching and landing on an airport nearby. 3) Operation procedures for two engines on the same side failed in flight a) Keep the aircraft attitude by banking the stick and applying the rudder to prevent the aircraft from banking and yawing. b) Set the throttle of normal engine to takeoff power condition, and keep the indicated aircraft speed not below 167kn~173kn (310~320km/h). After the aircraft attitude is stabilized, set the throttle to maximum continuous power condition. c) Balance the aircraft with trim tab to eliminate part of the load on the control stick and rudder. d) If the engine cannot feather automatically, manual feathering button should be used immediately. e) The landing gear, flaps and door should be retracted and closed immediately if they are in the extended and open positions. f) Pull the throttle of the faulty engine back to 0o. g) Set the shutdown switch to SHUTDOWN position and turn off the anti-fire switch. h) Extinguish fire by force at the faulty engine and the lower section of the fairing with the second group of fire bottles according to the actual situation. i) When flying with two engines on the same side for a long time, pay attention to the balance of the fuel quantity between left and right tanks.
  61. 61. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-8 June 30, 2012 4) When flying horizontally at the altitude of 26247ft~32808ft (8000~10000m) with two engines shutdown, the indicated air speed must be kept at 173kn~178kn (320~330km/h) and descends gradually to the altitude of 11483ft~13123ft (3500~4000m), and keeps a level flight at the same altitude with IAS of 173kn (320km/h) to the nearby airport for landing. 5) If a quick descent is required, pull the throttle back to 16o ~20o position, and keep an indicated airspeed of 243kn (450km/h) for descending. (h) Visual landing with two engines failed on the same side 1) When performing a traffic pattern flight with two engines failed on the same side, keep the indicated speed of 173kn~178kn (320~330km/h) with their propellers feathered and landing gears retracted. Reduce the load on the control stick and rudder with trim tab. When two engines on the same side fail, it is suggested to turn toward the normal engines and get into approach, or turn toward the failed engine and get into approach with a turning bank angle not more than 5o . The procedures for airline establishment are the same as the normal one except for landing gear down after the final turn. When getting into approach with crosswind of 16.4 ft/s~26.3 ft/s (5~8m/s), the failed engines side must be against the crosswind direction. 2) If the third and the fourth engines on the right side fail, extend landing gear urgently with left hydraulic system. 3) Perform the final turn with a turning bank angle not more than 15o and the indicated air speed of 162 kn~167 kn (300~310km/h). Keep gliding at a fine descent rate after turning, fly over the outer locator at the altitude 262 ft~328 ft (80~100m) higher than normal. Before flaring out, be sure to set the trim tab near the neutral position, so that the load on the control stick and rudder will increase. 4) When the indicated air speed is 157kn~162kn (290~300km/h) over the outer locator, lower the flap to 25o. After flying over the outer locator, if a successful approach can be assured by visual method, lower the flap to 35o, and then turn on the hydraulic communication valve. 5) Keep a speed of 135 kn~151 kn (250~280km/h) before flaring out as per different weight of aircraft, wind direction and speed. After flaring-out, pull the throttle back to 20o gently. Pull the inboard throttle back to 0o after the aircraft touches down. Lower the nose wheel and release the stop of inboard propellers when the direction gets stable. Pull the outboard throttle back to 0o, and keep the running direction with the rudder and the brakes.
  62. 62. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-9 June 30, 2012 6) When the running speed is lowered to 32 kn (60km/h), pull out the nose wheel steering handle, and then release the stop of outboard propellers. In this case, the distance of landing run will increase to 4265 ft~4921 ft (1300~1500m) as per different aircraft weight. 7) Cautions a) If the third and fourth engines on the right side fail, the nose wheel control and emergency brake is driven by left hydraulic system. If the first and the second engines on the left side fail, the normal brake is propelled by right hydraulic system. Therefore, when two engines on the same side fail, the hydraulic communication valve must be turned on. b) When flying with two engines on the same side, especially during landing, it’s better to reduce the throttles of the outboard engines and increase that of the inboard engines so as to reduce the load on the stick and rudder to maintain the desired flight condition. (i) Go around with two engines failed on the same side 1) When two engines on the same side fail and the propellers have feathered, go around could be performed under special condition with the air temperature of 30o C below, but the altitude must not be below 328 ft (100m), and flap should not be more than 25o . 2) If a go around is determined, the throttles of the operating engines should be advanced to the take-off power condition (100o+4 o -2 o ) rapidly, retract the landing gear and keep the indicated speed not below 151kn (280km/h). 3) When performing the go around with two engines failed on the same side, the most complicated action is that, when the throttles of the normal engines are advanced to takeoff power condition, large yawing moment and banking moment are produced on the aircraft against the failed engines. In order to overcome these two moments, the rudder should be deflected to the maximum angle, the ailerons to the position of 2/3 of the whole travel. In this case, the load on the rudder will increase to about 784N (80kgf) and that on the stick to about 294N (30kgf). When the rudder is set to the maximum angle, the aircraft will buffet. After retracting the landing gears, the aircraft speed increases rapidly, the deflecting angle of the rudder decreases, and the buffeting will disappear accordingly.
  63. 63. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-10 June 30, 2012 4) In order to reduce the rudder deflection and the load on it, bank the aircraft 7o ~8o toward the operating engine before the throttles advancement. When the indicated air speed is 162 kn (300km/h), retract the flaps in steps, and retard the throttles back to maximum continuous power condition. (j) Flight procedures with one outboard engine propeller in windmill condition 1) When the engine fails in flight and the entire propeller feathering systems fail, the propeller will be in a windmill condition. In this case, there will be a large yawing moment that makes the aircraft yaw and bank to the windmilling engine sharply, and decreases the aircraft speed by 10.8kn~13.5 kn (20~25km/h). 2) To keep the aircraft attitude and prevent the aircraft from yawing and banking, operate as follows: a) Press the helm, apply the rudder and keep the aircraft flying along straight line. b) Increase the operating engine throttle and keep the indicated air speed not below 162 kn (300km/h). c) Set the throttles of symmetrical operating engines to maximum continuous power condition or takeoff power condition, and pull the throttle of the operating engine symmetrical to the faulty one back to 40o ~60o at the same time. d) Reduce the load on the stick and rudder with trim tab. e) Retard throttle of the faulty engine back to 0o . f) Set the engine shutdown switch to SHUTDOWN position and turn off the anti-fire switch. 3) When the propeller of an outboard engine is in windmill condition, the load on the rudder will be about 882N (90kgf) and 343N (35kgf) on the stick. With the windmill speed stabilized to match the flight speed, the load on the rudder and stick will reduce by 50%. At this time, the load on the stick could be balanced wholly with trim tab, but the load on the rudder could not be completely balanced yet.
  64. 64. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-11 June 30, 2012 4) When the propeller of an outboard engine is in windmill condition, the aircraft can fly with three engines operating at the indicated speed of 178 kn (330km/h) and the altitude above 16404 ft (5000m). When the true airspeed is below 227kn (420km/h), the rotating speed of the propeller reaches to or approaches the balanced speed (95~96%), while the negative thrust of the propeller in windmill condition is not large. In fact, the drag of the propeller will not be affected by airspeed increase. If the aircraft flies at the altitude of 28528 ft (9000m), it must be descended gradually to an altitude of 19685ft~22966ft (6000~7000m) at the indicated speed of 184 kn~189 kn (340~350km/h). 5) When the aircraft enters the airport area and prepares to land, it must descend at the indicated speed of 162kn~173kn (300~320km/h). When it reaches to the altitude of about 16404 ft (5000m), the propeller should be free from the equilibrium speed, the indicated speed falls and the negative thrust of windmilling propeller be maximized. In this case, release the stop of the engine propeller from windmill condition to reduce the negative thrust, and provide favorable conditions for keeping the flight condition and controlling the landing. 6) At the moment of releasing the propeller stop (3~5s), the negative thrust increases in a short period, which brings an additional yawing and banking moment which causes the aircraft to yaw and bank. With the propeller windmill speed falling, the negative thrust is smaller than that with the propeller at a stop position, at this time, the aircraft speed increases slightly. To reduce the aircraft’s yawing and banking, bank the aircraft 7o ~8o to the contrary direction of the windmilling propeller before releasing the stop of the propeller. When an outboard engine propeller is in windmill condition (the stop released), retract the landing gears and the flaps, and keep the level flight condition at the indicated speed of 173 kn~178 kn (320~330km/h) under the altitude of 13123 ft (4000m). 7) Be aware that after the stop of the faulty engine propeller is released, the rotating speed begins to fall. Set the stop releasing switch to STOP position in 1~1.5s.
  65. 65. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-12 June 30, 2012 (k) Landing procedures with an outboard engine propeller in windmill condition (stop released) 1) The aircraft weights 49~51t, the air route altitude is 1640ft (500m), the indicated speed is kept at 173 kn (320km/h) with the landing gears up and at 157 kn~162 kn (290~300km/h) with the landing gears down. At this time, the throttles of the inboard operating engines are 72o ~84o , and the throttle of the outboard operating engine is about 40o ~60o . 2) Keep the indicated speed of 162kn~167 kn (300~310km/h) and a turning slope not more than 15o during the final turn. After that, extend the landing gears, keep gliding at a lower rate, and fly over the outer locator at an altitude 262 ft~328 ft (80~100m) higher than that in a normal condition. During gliding and before flaring out, be sure to set the ailerons and trim tab of rudder to or near their neutral position. 3) When flying over the outer locator, keep the indicated speed of 157kn~162kn (290~300km/h), lower the flaps to 25o , and adjust the indicated gliding speed to 140kn~151kn (260~280km/h). After flying over the outer locator, if a successful approach can be assured, lower the flaps to 35o . If there is a crosswind, correct it according to the crosswind correcting method. 4) Keep an indicated speed of 135kn~151kn (250~280km/h) before flaring out as per the weight of the aircraft, wind direction and speed. At this time, the throttle of the operating engine symmetrical to the faulty one is not less than 16o . After the aircraft touches down, pull the throttle of the operating engine symmetrical to the faulty one back to 0o gently. During this period, take special care to prevent the aircraft from yawing. 5) After the aircraft touches down, pull the throttles of the symmetrical operating engines back to 0o and release the stop. Keep the running direction with the rudder and brakes, and modify the aircraft yawing with the nose wheel steering handle if necessary. At the rear half of taxiing, when the aircraft speed is about 32.4kn (60km/h), pull out the nose wheel steering handle, and release the stop of the normal engine symmetrical to the faulty one. 6) Cautions: a) Because the windmill of one engine propeller brings a large negative thrust, the aircraft balancing requires a larger control surface deflection. So the aerodynamic performance of the aircraft deteriorates.
  66. 66. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-13 June 30, 2012 b) If an inboard engine fails and its propeller enters into windmill condition, the yawing and banking moment is much smaller than that from the windmill of an outboard engine. Therefore, it is easier to control an inboard engine windmilling in each stage of flight. (l) Landing procedures with an outboard engine propeller in windmill condition (blade angle 12o ) 1) If the propeller stop could not be released due to stop release system failure and windmill takes place with blade angle of 12o , the aircraft should fly to the nearest airport for landing. The altitude should be kept below 13123ft (4000m) and the indicated speed at 157 kn~162 kn (290~300km/h), the throttles of the two inboard engines should be retarded to 72o ~80o and the throttle of the outboard operating engine retarded to 40o ~60o . 2) When an outboard engine fails, the indicated speed is 189kn (350km/h) and the rudder deflection angle is more than 16o , the aircraft will buffet. To overcome the buffeting, bank the aircraft by 7o ~8o toward the two normal engines to reduce the rudder deflection angle and the load on the rudder. For example, bank 3o , and the load on the rudder can be reduced by 147N~196N (15kgf~20kgf), bank 7o ~8o , by 294N~392N (30 kgf~40kgf). Retarding the throttle of the normal engine symmetrical to the faulty one at the same time, the rudder deflection can also be reduced,but not less than 30o ~40o . 3) Keep level flight to perform the final turn. Descend after the final turn. 4) The operation procedure for the final leg is generally the same as the landing control procedure with the propeller stop released, except for a larger control surface deflection and load on the rudder and aileron. 5) When landing with the windmilling propeller, the aircrew should cooperate closely and try their best to avoid a go around regardless of the propeller status. Therefore, the specified altitude and air speed must be kept before the final turn. 6) Cautions a) The power of the normal engine symmetrical to the windmilling one could not be too large. If the throttle is over 40o , the rudder deflection would be more than 16o , which would bring division of the airflow on the control surface, and the aircraft would buffet violently.
  67. 67. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-14 June 30, 2012 b) To prevent the high-pressure fuel pump from being damaged, the windmilling of the engine is not allowed to exceed 10 minutes during flight training. (m) Go around with an outboard engine propeller in a windmill condition 1) Perform the go around if extremely necessary and the following conditions are all ready. a) Visual flight at an altitude not below 492ft (150m). b) The flap angle is not larger than 25o . c) The landing weight of the aircraft is not more than 53t. d) The air temperature is not higher than 25o C. 2) Operating procedures for go around: a) Advance the throttles of all normal engines to the takeoff power condition, and retract the landing gears and keep the flaps at 15o . b) Apply the rudder and bend the stick timely to prevent the aircraft from banking and yawing, bank the aircraft 4o ~5o toward the two normal engines. c) Climb at the indicated airspeed of 157 kn~162 kn (290~300km/h) with a climbing rate of 6.56ft/s~9.84ft/s (2~3m/s). d) Retract the flaps step by step. e) The co-pilot helps the pilot to keep and balance the attitude. f) Climb to the air route altitude and enter landing again. (n) Operation procedures when the aircraft glides to the altitude below 492 ft (150m) with an outboard engine failed 1) Landing before flaring-out: a) In the gliding before landing, if an outboard engine fails, the landing gears are extended, the flaps at 35o and the propeller at the stop position (blade angle is 12o ), the aircraft could continue landing along the gliding line. In this case, it is easier to stabilize and steer the aircraft. The deflection of the rudder and the aileron won’t exceed 2/3 of the whole travelling range. b) Apply the rudder and bend the stick in time to prevent the aircraft from banking and yawing and keep the aircraft attitude. c) Advance the inboard engine throttles, keep flying along the normal gliding line at the specified speed and retard the throttle of the normal engine symmetrical to the faulty one back to 30o ~40o .
  68. 68. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-15 June 30, 2012 d) Feather the failed engine with the manual-feathering button. e) Don’t use or use less the rudder and the aileron trim tabs to balance the aircraft. f) After feathering, the operating procedures are the same as those for landing with three engines in operation. g) If the feathering system fails, the stop of the propeller should not be released. Keep the indicated speed of 140kn~151kn (260~280km/h), and land in the same method with that the propeller is in windmill condition. 2) Landing with an outboard engine failed during flaring-out a) Apply the rudder and bend the stick in time to prevent the aircraft from banking, yawing and deviating from the runway. b) Retard all engines throttles back to 0o and release the propellers stop of the inboard engines after the aircraft touches down. During running, lower the nose wheel down to the ground and keep direction with the rudder. If necessary, correct the direction with the brake or pull out the nose wheel steering handle when the speed is below 81kn (150km/h). c) During the latter running with a speed below 32.4kn (60km/h), pull out the nose wheel steering handle and release the stop of the outboard propellers. 3) Cautions a) When the engine fails, the propeller is in windmill condition at the stop position (blade angle is 12o ), the landing gears are extended, the flaps are at 35o , and the flight altitude is over 492 ft (150m), the go around could be performed carefully. b) If an outboard engine fails and doesn’t feather, and the flaps are lowered at 35o , it is not necessary to retract the flaps. Keep the previous flight condition for gliding and landing. c) If the engine fails before lowering the flaps, after flying over the outer locator, if a successful approach can be assured, lower the flap to the required position. d) Be careful to keep the aircraft direction during landing and running.
  69. 69. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-16 June 30, 2012 HIGH ANGLE OF ATTACK FLIGHT The aircraft possesses better stability and controllability within the whole operating scope in terms of Mach number and C.G before the stalling angle of attack, regardless of the operating status of the landing gears and flaps. The aircraft can recover from stalling in any flying state by pushing the stick over its neutral position once the stalling phenomenon occurs in flight. It is prohibited to fly at high angle of attack. Since the aircraft mainly flies at high altitude near its service ceiling, the conditions that cause the aircraft stalling depend on the flight state, altitude and airspeed. The stall margin of angle of attack at high altitude is much less than that of flight at middle altitude. High angle of attack may occur in flight due to pilot’s misoperation during a sharp recovery of descending or when flying in a strong turbulent airflow and strong bomb explosive wave. To prevent the aircraft from stalling in flight, which is hazardous to flight safety, the pilots are required to understand the symptoms of the aircraft entering high angle of attack up and the operating technique for recovery, which is of great importance for the flight safety. Judgment on entering high angle of attack stall state The symptoms of aircraft stalling at minimum airspeed (a) When the airspeed of aircraft with its landing gears and flaps retracted decreases to 10.8 kn~13.5 kn (20~25km/h) before stalling, the vortex area on the wing surface enlarges rapidly, at this time the pilots feel the aircraft buffeting obviously, the left wing sinks and then the nose sinks. (b) When the aircraft with its landing gears and flaps lowered (flap setting 25o for taking-off and 35o for landing) nears its stalling state, there is no obvious warning symptom. Only a not obvious buffet appears at the moment when the aircraft stall occurs. It is difficult for the aircraft to get into the stalling state at later stage of the level flight after flaring-out (the throttles of the inboard engines are retarded to 0o position and those of the outboard engines to 16o ~20o position, flaps at 35o position).
  70. 70. JZ-Y8F200W-02 AIRCRAFT FLIGHT MANUAL SECTION III EMERGENCY PROCEDURES 3-17 June 30, 2012 The symptoms of the aircraft stalling in operating airspeed range Stall of the aircraft not only occur in stalling airspeed state but also in the whole operating airspeed range. Stalling may be caused by pulling back the stick too hard or flying in airflow where strong vertical disturbance and bump exist. It depends on the flight conditions and state of the flight. Stalling symptoms of the aircraft varies with different Mach numbers. The stalling of the wing (the left wing stalls first) and the sinking of nose are both slower when flying with a Mach number less than 0.45~0.5. When Mach number is 0.55~0.66, the stalling of wing and sinking of the nose develop drastically and aircraft buffet is also serious before the aircraft stalling (2o ~3o less than stalling angle). The general symptom is not obvious for the aircraft at large angle of attack. To ensure the safety of the aircraft and prevent the aircraft from entering stalling angle, an indicator of critical angle of attack is furnished on the aircraft which warns the pilot with its light and sound signal that the aircraft comes near the stalling state. Table 3-1 shows the angle of attack at which the warning will be given by the critical angle of attack indicator for different flap settings and Mach numbers. Table 3-1a Angle of attack at which the warning will be given by the critical angle of attack indicator Flap setting Flight status Takeoff and landing M number Altitude (ft) 0.2 0.3 0.5 0.6 0.65 0 17o 15.4o 11.1o 10.4o 10.5o 3281 15.4o 11.1o 10.4o 10o 3281 above 10.4o 10o Table 3-1b Angle of attack at which the warning will be given by the critical angle of attack indicator Flap setting Flight status Takeoff and landing M number Altitude (m) 0.2 0.3 0.5 0.6 0.65 0 17o 15.4o 11.1o 10.4o 10.5o 1000 15.4o 11.1o 10.4o 10o 1000 above 10.4o 10o
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