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9.1-1 1

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Rev. 0

F M S 9.11

SUPPLEMENT FOR

CATEGORY A OPERATIONS

When operating the helicopter in CATEGORY A, this supplement shall be attached to the

EC 135 Flight Manual (Section 9).

NOTE Due to the nature of its content, this supplement is divided into five separate,

related subsections that first present General Data applicable to all Category A

Operations and then specific data applicable to approved types of operation.

Date: 16.10.2006 Approved by EASA

EASA approval no.: R.C.01972

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LIST OF EFFECTIVE PAGES

NOTE N, R, or Dindicate pages which are New, Revised or Deleted respectively. Remove and dis-

pose of superseded pages, insert the latest revision pages and complete the Record of Sup-

plement-Revisions as necessary.

LEP EASA approved (part 1):

Page Rev.No. Rem Page Rev.No. Rem Page Rev.No. Rem

9.1-1 -1 0 R 9.1-1 -44 11 9.1-1 -86 10

R 9.1-1 -2 11 9.1-1 -45 10 9.1-1 -87 10

R 9.1-1 -3 11 9.1-1 -46 10 9.1-1 -88 10

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9.1-1 -40 6 9.1-1 -84 10 9.1-1 -128 109.1-1 -43 10 9.1-1 -85 10 9.1-1 -129 10

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LEP manufacturers data (part 2):

Page Rev.No. Rem Page Rev.No. Rem Page Rev.No. Rem

9.1-1 -41 / 6 9.1-1 -92 10 9.1-1 -131 /

10

(-42 blank) 9.1-1 -107 /

10 (-132 blank)

9.1-1 -66 10 (-108 blank)

LOG OF REVISION

FIRST ISSUE

ORIGINAL OCT 16, 2006

REVISION 1 NOV 27, 2007

(EASA APPROVAL NO. R.A.01375)

REVISION 2 MAY 06, 2008


REVISION 3 DEC 05, 2008


REVISION 4 JUL 30, 2009(EASA APPROVAL NO. R.C.03300)

REVISION 5 FEB 10, 2010

(EASA APPROVAL NO. 10028806)

REVISION 6 MAR 17, 2010(EASA APPROVAL NO. 10029296)

REVISION 7 JUN 24, 2010


REVISION 8 MAR 17, 2011


REVISION 9 AUG 04, 2011


REVISION 10 DEC 16, 2011(EASA APPROVAL NO. 10037712)

REVISION 11 (see entry below)

REVISION 11

Date: DEC 18, 2012 Approved by EASA

EASA approval no.: 10042758

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TABLE OF CONTENTS

A GENERAL DATA 9.11-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.1 GENERAL 9.11-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.1.1 Introduction 9.11-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.1.2 Abbreviations 9.11-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.1.3 Definitions 9.11-12. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2 LIMITATIONS 9.11-14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.1 Power check 9.11-14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.2 Configuration requirements 9.11-14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.3 HIGH NR mode 9.11-14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.4 Operational compatibility 9.11-14. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.5 CAT A operation in conjunction with IFR operation 9.11-15. . . . . . . . . . . . . . . . . .

A.2.6 Ambient air temperature limitations 9.11-15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.7 Altitude limitations 9.11-15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.8 Wind limitations 9.11-15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.9 T/O and landing envelope 9.11-16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.3 EMERGENCY AND MALFUNCTION PROCEDURES 9.11-19. . . . . . . . . . . . . . .

A.3.1 Single engine failure during takeoff 9.11-19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .A.3.2 Single engine failure prior to or during landing 9.11-19. . . . . . . . . . . . . . . . . . . . . .

A.3.3 30 sec/ 2min Topping Selection 9.11-19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.4 NORMAL PROCEDURES 9.11-19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.4.1 Takeoff 9.11-19. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.4.2 Before Landing 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5 PERFORMANCE DATA 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5.1 Power check 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5.2 Wind information 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5.3 Hight gain over a horizontal distance 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5.3.1. OEI climb performance 9.11-20. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.5.3.2. Influence of significant turns during OEI climb 9.11-21. . . . . . . . . . . . . . . . . . . . . .

A.5.3.3. OEI climb performance with optional equipment installed 9.11-21. . . . . . . . . . . .

A.5.4 En-route flight with one engine inoperative (OEI) 9.11-36. . . . . . . . . . . . . . . . . . . .

A.6 MASS AND BALANCE 9.11-41. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.7 SYSTEMS DESCRIPTION 9.11-41. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.8 HANDLING, SERVICE AND MAINTENANCE 9.11-41. . . . . . . . . . . . . . . . . . . . . .

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B CLEAR HELIPORT 9.11-43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.1 GENERAL 9.11-43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.1.1 Definitions 9.11-43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.2 LIMITATIONS (In addition to limitations given in part A) 9.11-43. . . . . . . . . . .

B.2.1 Certification criteria 9.11-43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.2.2 Mass limitations 9.11-43. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.3 EMERGENCY AND MALFUNCTION PROCEDURES 9.11-50. . . . . . . . . . . . . . .

B.3.1 One engine inoperative prior to TDP 9.11-50. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.3.2 One engine inoperative after TDP 9.11-51. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .B.3.3 One engine inoperative prior to LDP 9.11-52. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.3.4 One engine inoperative after LDP 9.11-53. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4 NORMAL PROCEDURES 9.11-54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.1 Takeoff 9.11-54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.1.1 Standard type takeoff flight path 9.11-54. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.1.2 Standard type takeoff procedure 9.11-55. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.2 Landing 9.11-56. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.2.1 Standard type landing flight path profile 9.11-56. . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.4.2.2 Standard type landing flight path procedure 9.11-57. . . . . . . . . . . . . . . . . . . . . . . .

B.5 PERFORMANCE DATA 9.11-58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.1 Takeoff performance 9.11-58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.1.1 Assured minimum flight conditions 9.11-58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.1.2 Takeoff distance required 9.11-58. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.1.3 OEI climbout flight path 9.11-61. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.2 Landing performance 9.11-64. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.5.2.1 Landing distance from a 50-ft height to a complete stopon the ground 9.11-64. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.6 MASS AND BALANCE 9.11-66. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.7 SYSTEM DESCRIPTIONS 9.11-66. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

B.8 HANDLING, SERVICING AND MAINTENANCE 9.11-66. . . . . . . . . . . . . . . . . . . .

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C VTOL (1)- SURFACE LEVEL OR ELEVATED HELIPORTS 9.11-67. . . .

C.1 GENERAL 9.11-67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.1.1 Definitions 9.11-67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.2 LIMITATIONS (In addtion to limitations given para A) 9.11-67. . . . . . . . . . . . .

C.2.1 Certification criteria 9.11-67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.2.2. Surface heliport 9.11-67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.2.3 Mass limitations 9.11-67. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.2.3.1 Mass limitations with optional equipment installed 9.11-68. . . . . . . . . . . . . . . . . . .

C.3 EMERGENCY AND MALFUNCTION PROCEDURES 9.11-72. . . . . . . . . . . . . . .

C.3.1 Surface level or elevated heliport One engine inoperativeprior to TDP 9.11-72. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.3.2 Surface level or elevated heliport One engine inoperativeafter TDP 9.11-73. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.3.3 Surface level or elevated heliport One engine inoperativ

prior to LDP 9.11-74. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.3.4 Surface level or elevated heliport One engine inoperative

after LDP 9.11-75. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .C.4 NORMAL PROCEDURES 9.11-76. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.4.1 Surface level or elevated heliport Vertical takeoff 9.11-76. . . . . . . . . . . . . . . . . .

C.4.2 Surface level or elevated heliport Vertical landing 9.11-82. . . . . . . . . . . . . . . . .

C.5 PERFORMANCE DATA 9.11-85. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.1 Climbout performance 9.11-85. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.1.1 Climbout flight path segments I and II 9.11-85. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.1.2 OEI takeoff distances - Surface level or elevated heliports 9.11-87. . . . . . . . . . .

C.5.2 Modified flight path to clear high obstacles 9.11-88. . . . . . . . . . . . . . . . . . . . . . . . .

C.5.2.1 Modified takeoff flight path 9.11-88. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.2.1.1 Distance from heliport to obstacle is less than the takeoffdistance required 9.11-88. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.2.1.2 Distance from heliport to obstacle is greater than the continuedtakeoff distance required 9.11-89. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.5.2.1.3 Distance from heliport to obstacle (Rearward T/O) 9.11-91. . . . . . . . . . . . . . . . .

C.5.2.2 Modified landing flight path 9.11-91. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.6 MASS AND BALANCE 9.11-92. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.7 SYSTEM DESCRIPTIONS 9.11-92. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

C.8 HANDLING, SERVICING AND MAINTENANCE 9.11-92. . . . . . . . . . . . . . . . . . . .

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E VTOL (3) - CONFINED HELIPORT 9.11-109. . . . . . . . . . . . . . . . . . . . . . . . . .

E.1 GENERAL 9.11-109. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.1.1 Definitions 9.11-109. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.2 LIMITATIONS (In addition to limitations given in para A) 9.11-109. . . . . . . .

E.2.1 Certification criteria 9.11-109. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.2.2 Mass limitations 9.11-109. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.2.2.1. Mass limitations with optional equipment installed 9.11-110. . . . . . . . . . . . . . . . . .

E.3 EMERGENCY AND MALFUNCTION PROCEDURES 9.11-114. . . . . . . . . . . . . .

E.3.1 Confined heliport - One engine inoperative prior to TDP 9.11-114. . . . . . . . . . . .

E.3.2 Confined heliport - One engine inoperative after TDP 9.11-116. . . . . . . . . . . . . .

E.3.3 Confined heliport One engine inoperative prior to LDP 9.11-118. . . . . . . . . . . .

E.3.4 Confined heliport One engine inoperative after LDP 9.11-119. . . . . . . . . . . . . .

E.4 NORMAL PROCEDURES 9.11-120. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.4.1 Confined heliport - Vertical takeoff 9.11-120. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.4.2 Confined heliport Vertical landing 9.11-124. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.5 PERFORMANCE DATA 9.11-126. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.5.1 Climbout performance 9.11-126. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.5.1.1 OEI climbout flight path segments I and II 9.11-126. . . . . . . . . . . . . . . . . . . . . . . . .

E.5.1.2 Heights and distances - VTOL confined heliport 9.11-128. . . . . . . . . . . . . . . . . . .

E.5.1.2.1 Heights and distances - Modified Flight Path forVTOL confined heliport 9.11-129. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.6 MASS AND BALANCE 9.11-131. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.7 SYSTEM DESCRIPTIONS 9.11-131. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

E.8 HANDLING, SERVICING AND MAINTENANCE 9.11-131. . . . . . . . . . . . . . . . . . .

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9.1-1 9

EASA APPROVED

Rev. 10

LIST OF FIGURES

Fig. A1 Flight Envelope 9.11- 16. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. A2 Flight Envelope Sandfilter installed 9.11- 17. . . . . . . . . . . . . . . . . . . . . . . . . .Fig. A3 Flight Envelope IBF System installed 9.11- 18. . . . . . . . . . . . . . . . . . . . . . . . .

Fig. A4 Climbout flight path segment I, 35ft to 200 ft AGL, Gross Mass1500kg to 2100kg 9.11- 23. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .


Fig. A6 Climbout flight path segment I, 35ft to 200 ft AGL, Gross Mass1500kg to 2100kg Sandfilter installed 9.11- 25. . . . . . . . . . . . . . . . . . . . . . . .

Fig. A7 Climbout flight path segment I, 35ft to 200 ft AGL, Gross Mass2100kg to 2500kg Sandfilter installed 9.11- 26. . . . . . . . . . . . . . . . . . . . . . . . .


Fig. A9 Climbout flight path segment I, 35ft to 200 ft AGL, Gross Mass2500kg to 2910kg Sandfilter installed 9.11- 29. . . . . . . . . . . . . . . . . . . . . . . .

Fig. A10 Climbout flight path segment II, 200 ft to 1000 ft AGL, Gross Mass1500kg to 2100kg 9.11- 30. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



Fig. A13 Climbout flight path segment II, 200 ft to 1000 ft AGL, Gross Mass1500kg to 2100kg Sandfilter installed 9.11- 33. . . . . . . . . . . . . . . . . . . . . . . .



Fig. A16 Maximum gross mass for OEI enroute flight 9.11- 39. . . . . . . . . . . . . . . . . . .

Fig. A17 Maximum gross mass for OEI en-route flight Sandfilter installed 9.11- 40.

Fig. B1 Maximum takeoff and landing gross mass 9.11- 47. . . . . . . . . . . . . . . . . . . . . .

Fig. B2 Maximum takeoff and landing gross mass Sandfilter installed 9.11- 48. . .

Fig. B3 Maximum takeoff and landing gross mass IBF System installed 9.11- 49.

Fig. B4 OEI rejected takeoff profile - Clear heliport 9.11- 50. . . . . . . . . . . . . . . . . . . . .

Fig. B5 OEI continued takeoff profile - Clear heliport 9.11- 51. . . . . . . . . . . . . . . . . . . .

Fig. B6 OEI balked landing profile - Clear heliport 9.11- 52. . . . . . . . . . . . . . . . . . . . . .

Fig. B7 OEI landing profile - Clear heliport 9.11- 53. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. B8 Standard type takeoff flight path profile - Clear heliport 9.11- 54. . . . . . . . . . .

Fig. B9 Standard type landing flight path profile - Clear heliport 9.11- 56. . . . . . . . . .

Fig. B10 Rejected takeoff distance required 9.11- 59. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. B11 Continued takeoff distance required 9.11- 60. . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. B12 Acceleration distance VTOSSto VY 9.11- 62. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. B13 OEI climbout profile - Clear heliport 9.11- 63. . . . . . . . . . . . . . . . . . . . . . . . . . . .Fig. B14 Landing distance from 50ft height to a complete stopon the ground. 9.11- 65

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9.1-1 10

EASA APPROVED

Rev. 10

Fig. C1 Maximum takeoff and landing gross mass (VTOL) 9.11- 69. . . . . . . . . . . . . .

Fig. C2 Maximum takeoff and landing gross mass (VTOL) Sandfilterinstalled 9.11- 71. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C3 Maximum takeoff and landing gross mass (VTOL) IBF Systemrinstalled 9.11- 71. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C4 OEI rejected takeoff profile (Surface level or elevated heliport) 9.11- 72. . .

Fig. C5 OEI continued takeoff profile (Surface level or elevated heliport) 9.11- 73. .

Fig. C6 OEI balked landing profile (Surface level or elevated heliport) 9.11- 74. . . . .

Fig. C7 OEI landing profile (Surface level or elevated heliport) 9.11- 75. . . . . . . . . . .

Fig. C8 Vertical takeoff profile (Surface level or elevated heliport) 9.11- 77. . . . . . . . .

Fig. C9 Heliport sight picture at 50 ft AHE (Surface level heliport) h/c with basic instrument panel 9.11- 78. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C10 Heliport sight picture at 50 ft AHE (Surface level heliport) h/c with extended instrument panel 9.11- 78. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C11 Heliport sight picture at 120 ft AHE (Surface level heliport) h/c with basic instrument panel 9.11- 79. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C12 Heliport sight picture at 120 ft AHE (Surface level heliport) h/c with extended instrument panel 9.11- 79. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C13 Heliport sight picture at 50 ft AHE (Elevated heliport) h/c with basic instrument panel 9.11- 80. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C14 Heliport sight picture at 50 ft AHE (Elevated heliport) h/c with extended instrument panel 9.11- 80. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C15 Heliport sight picture at 120 ft AHE (Elevated heliport) h/c with basic instrument panel 9.11- 81. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C16 Heliport sight picture at 120 ft AHE (Elevated heliport) h/c with extended instrument panel 9.11- 81. . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C17 Vertical landing profile (Surface level or elevated heliport) 9.11- 83. . . . . . . .

Fig. C18 Heliport sight picture at 120 ft AHE (LDP) (Surface level orelevated heliport) h/c with basic instrument panel 9.11- 83. . . . . . . . . . . . . .

Fig. C19 Heliport sight picture at 120 ft AHE (LDP) (Surface level orelevated heliport) h/c with extended instrument panel 9.11- 84. . . . . . . . . .

Fig. C20 Acceleration distance VTOSSto VY 9.11- 85. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C21 OEI climbout profile (VTOL) 9.11- 86. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Fig. C22 Continued takeoff flight path (Surface level or elevated heliport) 9.11- 87. . .

Fig. C23 Rearward flight path (VTOL) 9.11- 91. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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GENERALDATA

9.1-1 12

EASA APPROVED

Rev. 0

A. GENERAL DATA

A.1. GENERAL

A.1.1. INTRODUCTION

The information presented in this supplement - required for Category A operations -

complements the information of the approved basic sections 1 through 5. For limitations,

procedures and performance data not contained herein refer to the respective preceding

sections of this manual.

The information presented in this supplement are required for the following approved

types of operations:

Clear Heliport

VTOL (1) Surface Level or Elevated Heliport

VTOL (2) Short Field

VTOL (3) Confined Heliport

A.1.2. ABBREVIATIONS

AHE - Above Helipad Elevation

IP - Intermediate Point

LDP - Landing Decision Point

MAT - Mass/Altitude/Temperature

TDP - Takeoff Decision Point

TOGM - Takeoff Gross Mass

VTOSS - Takeoff Safety Speed

VTOL - Vertical Takeoff and Landing

A.1.3. DEFINITIONS

Category A Takeoff is determined so that, if one engine fails at any time after the start

of takeoff, the aircraft can

prior to TDP return to and stop safely on the takeoff area, or

after TDP continue the takeoff and climb out and attain single-engine forward flight.

Category A Landing is determined so that, if one engine fails at any point in the ap-

proach path, the aircraft can

prior to LDP climb-out from the point of engine failure and attain single-engine for-

ward flight or continue the approach and stop safely on the landing area, or afterLDP continue the approach and stop safely on the landing area.

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GENERALDATA

9.1-1 13

EASA APPROVED

Rev. 0

Takeoff Decision Point (TDP)is the first point from which a continued takeoff capability

is assured and is the last point in the takeoff path from which a rejected takeoff is as-

sured within the determined rejected takeoff distance.

Landing Decision Point (LDP) is the last point in the approach and landing path from

which a balked landing can be accomplished.

Continued Takeoff Distanceis the horizontal distance along the takeoff flight path from

the start of the takeoff to the point at which the helicopter attains and remains at least 35

feet above the takeoff surface, attains and maintains a speed of at least V TOSS, and es-

tablishes a positive rate of climb.

Rejected Takeoff Distance is the horizontal distance necessary to stop safely the heli-

copter when one engine becomes inoperative prior to TDP.

Clear Heliport Landing Distance Required is the horizontal distance necessary for a

helicopter with one engine inoperative to land and come to a complete stop from a point

50 ft above the landing surface.

Takeoff Segment IDistance is the horizontal distance necessary to climb with VTOSSfrom the end of the takeoff distance to 200 ft AGL.

Takeoff Segment IIDistance is the horizontal distance necessary to climb with VYfrom200 ft to 1000 ft AGL.

Takeoff Safety Speed (VTOSS )means a referenced airspeed obtained after takeoff at

which the required oneengineinoperative climb performance can be achieved (steady

R/C of at least 100 ft/min with 2 min/30sec power (OEI) to 200 ft AHE).

VTOSS= 40 KIAS

Best Rate-of-climb Speed(VY)is the airspeed which leads to the greatest gain in alti-

tude in a specified period of time.

VY= 65 KIAS

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GENERALDATA

9.1-1 15

EASA APPROVED

Rev. 8

A.2.5. CAT A OPERATION IN CONJUNCTION WITH IFR OPERATION

Category A takeoff:

Weather conditions must be such that the CAT A takeoff profile can be followed and the

aircraft accelerated to VYin VMC.

Category A landing:

Weather conditions must be such that the aircraft can be decelerated from the IFR ap-

proach minimums to the CAT A LDP conditions or abort the landing and accelerate back

to VYin VMC.

A.2.6. AMBIENT AIR TEMPERATURE LIMITATIONS

Minimum air temperature is 35_

C. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maximum air temperature is ISA+ 39 _C. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

(max. + 50_C)

Maximum air temperature with Sandfilter

(FMS 9.239) installed is ISA+ 27_C. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Maximum air temperature with INLET BARRIER FILTER (IBF System)

(FMS 9.293) installed is ISA+ 35_C (max. + 45_C). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

A.2.7. ALTITUDE LIMITATIONS

Maximum T/O and landing altitude for Clear Heliport operations is 12000 ft DA/PA. . . . . .

Maximum T/O and landing altitude

for VTOL is 8000 ft DA/PA,. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

whichever is less

A.2.8. WIND LIMITATIONSCategory A takeoff and landing procedures are prohibited for flight conditions with tail-

wind components.

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GENERALDATA

9.1-1 16

EASA APPROVED

Rev. 5

A.2.9. TAKEOFF AND LANDING ENVELOPE (observe Fig. A1, A2 and A3)

OAT [_C]

MAX. ENVELOPE FOR CAT A TAKEOFF AND LANDING

Fig. A1 T/O and landing envelope (1)

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GENERALDATA

9.1-1 17

EASA APPROVED

Rev. 0

MAX. ENVELOPE FOR CAT A TAKEOFF AND LANDING SANDFILTER INSTALLED

Fig. A2 T/O and landing envelope Sandfilter installed (2)

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GENERALDATA

9.1-1 18

EASA APPROVED

Rev. 8

MAX. ENVELOPE FOR CAT A TAKEOFF AND LANDING IBF SYSTEM INSTALLED

Fig. A3 T/O and landing envelope IBF System installed (3)

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GENERALDATA

9.1-1 19

EASA APPROVED

Rev. 5

A.3. EMERGENCY AND MALFUNCTION PROCEDURES

NOTE Steady parts of the procedures are established with not less than 97% rotor

rpm. The transient values are only allowed to cushion the landing.

A.3.1. SINGLE ENGINE FAILURE DURING TAKEOFF

If one engine fails prior to TDP the takeoff must be rejected.

If one engine fails after TDP the takeoff must be continued.

A.3.2. SINGLE ENGINE FAILURE PRIOR TO OR DURING LANDING

If one engine fails prior to LDP the pilot may elect to balk the landing or to continue the

approach.

If one engine fails after LDP the landing must be continued.

NOTE For detailed information concerning CAT A emergency procedures after an en-

gine failure see para. 3 in the subsections (BE) of this supplement.

A.3.3. 30 SEC./ 2 MIN. TOPPING SELECTION

A TOPPING pushbutton on collective pitch panel provides selection between 30 sec-

onds and 2 minutes power limitations. After an engine failure, the 30 seconds power lim-

its are set by default.

A.4. NORMAL PROCEDURES

NOTE For detailed information concerning CAT A normal procedures see para. 4 in the

subsections (BE) of this supplement.

EFFECTIVITY If INLET BARRIER FILTERSYSTEM (IBF System), FMS 9.293, is installed

A.4.1. TAKEOFF

Before takeoff if IBF System NORM:

Both engines IDLE

RECALL sw Press

If last contamination is greater than 3 green bargraphs

BYPASS sw 1 and 2 OPEN

SANDFILT advisory Check off

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GENERALDATA

9.1-1 20

EASA APPROVED

Rev. 5

A.4.2. BEFORE LANDING

Final Approach (before LDP) if IBF System NORM

RECALL sw Press

If last contamination is greater than 3 green bargraphs

BYPASS sw 1 and 2 OPEN

SANDFILT advisory Check off

EFFECTIVITY All

A.5. PERFORMANCE DATA

A.5.1. POWER CHECK

For power check diagrams refer to basic manual, Section 5.

If Sandfilter or IBF System is installed, observe the additional power check information,

provided in the corresponding FMS 9.239 (Sandfilter) and FMS 9.293 (IBF System).

A.5.2. WIND INFORMATION

Wind accountability is UNFACTORED.

NOTE Unless otherwise authorized by operating regulations, the pilot is not authorized

to credit more than the performance increase resulting from 50% of the actual

headwind component.

Controllability for Category A takeoff and landing procedures has been demonstrated for

flight conditions with crosswind components up to 17 kt.

A.5.3. HEIGHT GAIN OVER A HORIZONTAL DISTANCE

A.5.3.1. OEI climb performance

OEI climb performance charts (see also Section 5 of the basic Flight Manual) are pre-

sented for OEI/MCP and 2.0-min/30-sec power ratings at different airspeeds (VY and

VTOSS). These charts show height gain data as functions of takeoff pressure altitude, out-

side air temperature and gross mass.

NOTE The height gain charts over a horizontal distance are based on the takeoff alti-

tude. The read out height gains are valid in segment I from the takeoff altitude

up to 200 ft above it, and for segment II from the takeoff altitude up to 1000 ftabove it.

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GENERALDATA

9.1-1 21

EASA APPROVED

Rev. 11

A.5.3.2. Influence of significant turns during OEI climb

The performance data fig. A4 to fig. A15 apply to climbs without any significant bank

angle. The following table shows the reduction in height gain over a horizontal distance

of 100 ft in the takeoff climbout flight path (valid for all combinations of gross mass/alti-

tude/OAT):

nHeight Gain / OEI (ft /100 ft)

Bank angle 15_ Bank angle 30_

Segment II 65 KIAS (VY) 1.5 8

NOTE In segment I a turn limited to 10_ bank angle is authorized without change in

height gain.

A.5.3.3. OEI climb performance with optional equipment installed

Category A OEI climb performance is influenced by following external mounted optional

equipment:

*

nHeight Gain (HG) OPTIONAL EQUIPMENT*

GM2720 kg GM > 2720 kg

Emergency Floatation System on NormalLanding Gear (FMS 9.2-67)

0.30 ft/ 100ft 0.25 ft/ 100ft

Emergency Floatation System on IntermediateLanding Gear (FMS 9.2-67 and 9.294)

0.40 ft/ 100ft 0.35 ft/ 100ft

Searchlight SX-16 (Front) (FMS 9.2-13) 0.35 ft/ 100ft 0.30 ft/ 100ft

Searchlight SX-16 (Side) (FMS 9.2-52) 0.55 ft/ 100ft 0.45 ft/ 100ft

External Loudspeaker (FMS 9.2-18) 0.60 ft/ 100ft 0.50 ft/ 100ft

FLIR (Irenco Leo II) (FMS 9.2-45) 0.30 ft/ 100ft 0.25 ft/ 100ft

FLIR (Wescam) (FMS 9.2-10) 0.30 ft/ 100ft 0.25 ft/ 100ft

HF 9000 (FMS 9.2-90) 0.30 ft/ 100ft 0.25 ft/ 100ft

FLIR Ultraforce LEO II (FMS 9.2-72) 0.30 ft/ 100ft 0.25 ft/ 100ft

FLIR LEOIIIHD (FMS 9.2-101) 0.25 ft/ 100ft 0.20 ft/ 100ft

FLIR Mx15i (FMS 9.2-89) 0.35 ft/ 100ft 0.30 ft/ 100ft

FLIR Star Safire HD System (FMS 9.2-92) 0.30 ft/ 100ft 0.25 ft/ 100ft

EOS Star Safire 380-HD (FMS 9.2-106) 0.30 ft/ 100ft 0.25 ft/ 100ft

External Hoist System (FMS 9.2-20) 0.35 ft/ 100ft 0.30 ft/ 100ft

Snow Skids on High Landing Gear(FMS 9.2-41 and 9.222)

0.30 ft/ 100ft 0.25 ft/ 100ft

Snow Skids on Intermediate Landing Gear(FMS 9.2-41 and 9.294)

0.25 ft/ 100ft 0.20 ft/ 100ft

Modified Access Panel 505 Cargo Hook(FMS 9.2-19 or 9.247)1)

0.25 ft/ 100ft 0.20 ft/ 100ft

Cargo Hook (FMS 9.2-19 or 9.247)2) 0.30 ft/ 100ft 0.25 ft/ 100ft

Cargo Hook and External Mirror Assy RHside(FMS 9.2-19 or 9.247)2)

0.60 ft/ 100ft 0.50 ft/ 100ft

Cargo Hook and External Mirror Assy LHside

(FMS 9.2-19 or 9.247) 2) 0.60 ft/ 100ft 0.50 ft/ 100ft

Continued:

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GENERALDATA

9.1-1 22

EASA APPROVED

Rev. 10

*

nHeight Gain (HG) OPTIONAL EQUIPMENT*

GM2720 kg GM > 2720 kg

Cargo Hook and External Mirror Assy on both

sides (FMS 9.2-19 or 9.247) 2) 0.90 ft/ 100ft 0.75 ft/ 100ft

HELLAS System (FMS 9.2-68) 0.35 ft/ 100ft 0.30 ft/ 100ft

EVS 1500 (FMS 9.2-96) 0.10 ft/ 100ft 0.10 ft/ 100ft

4 Additional LED Landing Lights (FMS 9.2-68) 0.35 ft/ 100ft 0.30 ft/ 100ft

IBF System (FMS 9.2-93) 0.30 ft/ 100ft 0.25 ft/ 100ft

* All results obtained from the OEI climb performance charts are to be corrected using these correction values.

1) without cargo hook and mirror(s) assy

2) with original or with modified access panel installed

EXAMPLE: (see Fig. A4)

Determine: OEI height gain over a horizontal distance of 100 ft (takeoff flight pathsegment I (35 ft to 200 ft AGL))

Known: Takeoff altitude 4600 ft. . . . . . . . . . . .

OAT 20 _C. . . . . . . . . . . . . . . . . . . . . . . .

Gross mass 2020 kg. . . . . . . . . . . . . . . .

Headwind 14 kt. . . . . . . . . . . . . . . . . . . .

for calculation (50%): Headwind 7 kt.

Airspeed VTOSS. . . . . . . . . . . . . . . . . . . . . . . .

External Optional Equipment None. . . . . .

Solution: Height gain = 33 ft

1. Enter chart at known pressure altitude (4600 ft)

2. Move horizontally right to known OAT (20_C)

3. Move vertically downwards to reference line.

4. Move further downwards following the gross mass guide lines.

5. Enter chart at known gross mass (2020 kg).

6. Move horizontally right to intersect tracing from above.

7. From point of intersection move vertically downwards to reference line.

8. Move further downwards following the headwind guide lines.

9. Enter chart at known headwind (7 kt).

10. Move horizontally right to intersect tracing from above.

11. From point of intersection move vertically downwards and read height gainover a horizontal distance of 100 ft (33 ft).

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GENERALDATA

9.1-1 23

EASA APPROVED

Rev. 5

CATEGORY A

CLIMBOUT FLIGHT PATH SEGMENT I (35 FT TO 200 FT AGL)

HEIGHT GAIN OVER A HORIZONTAL DISTANCE OF 100 FT

1 X PRATT & WHITNEY PW 206 B2

2.0 MIN. POWER (OEI) VTOSS= 40 KIAS

Fig. A4 Climbout flight path segment I, 35ft to 200ft AGL, Gross Mass 1500kg to 2100kg

NOTE: Wind accountability is unfactored

GROSSMASS

kg

TAKEOFFALTITUDEft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE

HEIGHT GAIN OVER A HORIZONTAL DISTANCE OF 100 FT ft

0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

8000 FTDENSITYALTITUDE

EC135P2S1514_

1


1500

1600

1700

1800

1900

2000

2100

2100KG1500KG

35 to 20

10 to 0

+10 to +20

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GENERALDATA

9.1-1 24

EASA APPROVED

Rev. 5

CATEGORY A







GROS

SMASS

kg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

1300014000

15000

EC135P2S1

514_

22500

2400

2300

2200

2100

2100KG2500KG



+10 to +20

10 to 0

35 to 20

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GENERALDATA

9.1-1 25

EASA APPROVED

Rev. 5

CATEGORY A



SANDFILTER INSTALLED1 X PRATT & WHITNEY PW 206 B2

2.0 MIN. POWER (OEI) BLEED AIR: OFF; VTOSS= 40 KIAS



GROSSM

ASS

kg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

1400015000


EC135P2S1514_1

SF


1500

1600

1700

1800

1900

2000

2100

2100KG1500KG

35 to 20

10 to 0

Observe temperature limitationISA+27_C if sandfilter installed

(see para. A.2.6)

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GENERALDATA

9.1-1 26

EASA APPROVED

Rev. 5

CATEGORY A







GROSS

MASS

kg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1514

_2SF

2500

2400

2300

2200

2100

2100KG2500KG



35 to 20

10 to 0


(see para. A.2.6)

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GENERALDATA

9.1-1 27

EASA APPROVED

Rev. 5

EXAMPLE: Additional example to use Height Gain diagram, with the possibility toverify max. gross mass for a determined climb gradient (for Fig. A8 orFig. A9 if sandfilter installed)

Determine: Maximum gross mass for a climb gradient of 8% (height gain 8 ft overa horizontal distance of 100ft);H/C operation at a public interest site

Known: Pressure altitude 4000 ft. . . . . . . . . . .

OAT 10 _C. . . . . . . . . . . . . . . . . . . . . . . .

Headwind 0 kt. . . . . . . . . . . . . . . . . . . . .

for calculation 50%: Headwind 0 kt. .

Airspeed VTOSS. . . . . . . . . . . . . . . . . . . . . . . .

External Optional Equipment None. . . . . .

Solution: Gross mass 2760 kg

1. Enter chart at known pressure altitude (4000 ft)

2. Move horizontally right to known OAT (10_C)

3. Move vertically downwards to reference line.

4. Move further downwards following the gross mass guide lines.

5. Enter lower chart (HEADWIND/HEIGHT GAIN) at known climb gradient(8%) move vertically upwards

6. Enter lower chart at known headwind (0 kt), move horizontally right to in-tersect tracing from below.

7. From point of intersection move upwards following the headwind guidelines to reference line ( not necessary for 0 headwind) and further verticallyupwards to intersect tracing from above.

8. From point of intersection move horizontally left and read maximum grossmass 2760 kg.

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GENERALDATA

9.1-1 28

EASA APPROVED

Rev. 5

CATEGORY A







GROSSMASSkg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

+10 to +20

10 to 0


EC135P2S1514_

3


35 to 20

2900

2800

2700

2600

2500

2500KG2910KG

3000 GROSS MASS LIMIT 2910 KG

Observe altitude limitations of:

D12000 ft if GM above 2720 kg


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GENERALDATA

9.1-1 29

EASA APPROVED

Rev. 6

CATEGORY A







GROSSMASS

kg

TAK

EOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

10 to 0


EC135P2S1514_3

SF

35 to 20

2900

2800

2700

2600

2500

2500KG2910KG

3000 GROSS MASS LIMIT 2910 KG


(see para. A.2.6)




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GENERALDATA

9.1-1 30

EASA APPROVED

Rev. 5

CATEGORY A

CLIMBOUT FLIGHT PATH SEGMENT II (200 FT TO 1000 FT AGL)

HEIGHT GAIN OVER A HORIZONTAL DISTANCE OF 100 FT1 X PRATT & WHITNEY PW 206 B2

MCP (OEI) BLEED AIR: OFF; VY= 65 KIAS

Fig. A10 Climbout flight path segment II, 200ft to 1000ft AGL, Gross Mass 1500kg to 2100kg


GROSSMASS

kg

TAKEOFFALTITUDEft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1516_

1

1500

1600

1700

1800

1900

2000

2100

2100KG1500KG



35 to 0

+10 to +30

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GENERALDATA

9.1-1 31

EASA APPROVED

Rev. 5

CATEGORY A





GROSSMASS

kg

TAKEOFFALTITUDEft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1516_

22500

2400

2300

2200

2100

2100KG2500KG

+10 to +30

35 to 0




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GENERALDATA

9.1-1 32

EASA APPROVED

Rev. 5

CATEGORY A





GROSSM

ASS

kg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

1400015000

EC135P2S1516_3

2500KG2910KG

3000

2900

2800

2700

2600

2500



35 to 0

+10 to +30

GROSS MASS LIMIT 2910 KG





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GENERALDATA

9.1-1 33

EASA APPROVED

Rev. 5

CATEGORY A







GROSSMASS

kg

TAKEOFFALTITUDEft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1516_

1SF

1500

1600

1700

1800

1900

2000

2100

2100KG1500KG


35 to 0

+10 to +30



(see para. A.2.6)

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GENERALDATA

9.1-1 34

EASA APPROVED

Rev. 5

CATEGORY A






GROSS

MASS

kg

TAKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1516

_2SF

2500

2400

2300

2200

2100

2100KG2500KG



35 to 0

+10 to +30


(see para. A.2.6)


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GENERALDATA

9.1-1 35

EASA APPROVED

Rev. 5

CATEGORY A






GROSS

MASS

kg

T

AKEOFFALTITUDE

ft

REFERENCE LINE

16000

17000

18000

30

10

HEADWIND

kt 20

0REFERENCE LINE


0 20 30 4010

0

5000

10000

1000

2000

3000

4000

6000

7000

8000

9000

11000

12000

13000

14000

15000

EC135P2S1516

_3SF

2500KG2910KG

3000

2900

2800

2700

2600

2500


35 to 0

+10 to +30




(see para. A.2.6)Observe altitude limitations of:




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GENERALDATA

9.1-1 36

EASA APPROVED

Rev. 11

A.5.4. ENROUTE FLIGHT WITH ONE ENGINE INOPERATIVE (OEI)

The maximum gross mass chart for OEI enroute flights is presented for OEI/MCP power

rating at VY= 65 KIAS. This chart shows the maximum gross mass that permits a rate of

climb of at least 50 ft/min at an height of 1000 ft AGL.

For maximum vertical takeoff and landing gross mass refer to Fig. A16 or, if sandfilter is

installed, to Fig. A17. However if external mounted optional equipment (shown below) is

installed, proceed as follows:

All results obtained from maximum takeoff and landing gross mass chart (Fig. A16

or A17) are to be corrected using these correction values:

Emergency Floatation System on Normal Landing Gear (FMS 9.2-67) subtract 25 kg

Emergency Floatation System on Intermediate Landing Gear

(FMS 9.2-67 and 9.294) subtract 35 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SX 16 Search Light (Front) (FMS 9.213) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . .

SX 16 Search Light (Side) (FMS 9.252) subtract 45 kg. . . . . . . . . . . . . . . . . . . . . . . . .

External Loudspeaker (FMS 9.2-18) subtract 50 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR (IRENCO) (FMS 9.2-45) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR (WESCAM) (FMS 9.2-10) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR Ultraforce LEO II (FMS 9.2-72) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR LEOIIIHD (FMS 9.2-101) subtract 20 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR Mx15i (FMS 9.2-89) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR Star Safire HD System (FMS 9.2-92) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . .

EOS Star Safire 380-HD (FMS 9.2-106) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . .

External Hoist System (FMS 9.2-20) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Snow Skids on High Landing Gear (FMS 9.2-41 and 9.222) subtract 25 kg. . . . . . . .

Snow Skids on Intermediate Landing Gear (FMS 9.2-41 and 9.294) subtract 20 kg.

Modified Access Panel 5051) (FMS 9.2-19 and 9.247) subtract 20 kg. . . . . . . . . . . . .

Cargo Hook 2)(FMS 9.2-19 and 9.247) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . .

Cargo Hook and LH External Mirror Assy 2) (FMS 9.2-19 and 9.247) subtract 50 kg

Cargo Hook and RH External Mirror Assy 2) (FMS 9.2-19 and 9.247) subtract 50 kg

Cargo Hook and both External Mirror Assy 2)(FMS 9.2-19 and 9.247) subtract 75 kg

HELLAS System (FMS 9.2-68) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HF 9000 (FMS 9.2-90) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EVS 1500 (FMS 9.2-96) subtract 10 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 Additional LED Landing Lights (FMS 9.2-97) subtract 30 kg. . . . . . . . . . . . . . . . . . . . .

IBF System (FMS 9.2-93) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



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GENERALDATA

9.1-1 37

EASA APPROVED

Rev. 10

If the ambient conditions (PA, OAT) are presented by a point located in the dashed area

of the diagram (extrapolated beyond the upper gross mass limit), the correction value(s)

may be subtracted from the gross mass value corresponding to that point.

However, the result must not exceed the upper gross mass limit of 2910 kg (2720

kg above 12000 ft PA and 2835 kg above 10000 ft PA )!

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GENERALDATA

9.1-1 38

EASA APPROVED

Rev. 6

EXAMPLE: (see Fig. A16)

Determine: Max. gross mass for OEI enroute flight

Known: OAT 22 _C. . . . . . . . . . . . . . . . . . . . . . . .

Pressure altitude 8000 ft. . . . . . . . . . . . .

Solution: Gross mass = 2585 kg

1. Enter chart at known OAT (22_C)

2. Move vertically upwards to to known pressure altitude (8000 ft)

3. Move horizontally left and read max. gross mass = 2585 kg

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GENERALDATA

9.1-1 39

EASA APPROVED

Rev. 6

Fig. A16 Maximum Gross Mass for OEI enroute flight

CATEGORY A ENROUTE FLIGHTOEI MCP VY= 65 KIAS

50 FT/MIN 1000 FT AGL BLEED AIR: OFF

OAT _C

GROSSMASSkg

0 10 20 40 5030 20 10 30

2400

2300

2200

2100

2000

1900

1800

1700

1600

2600

2500

2700

2800

EC135P2S1532_

1

40

2900

3000

MIN.

OAT

MAX.

OAT

12000 FT


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GENERALDATA

9.1-1 40

EASA APPROVED

Rev. 6

Fig. A17 Maximum Gross Mass for OEI enroute flight if sandfilter installed

CATEGORY A ENROUTE FLIGHT SANDFILTER INSTALLEDOEI MCP VY=65 KIAS

50 FT/MIN 1000 FT AGL BLEED AIR: OFF

OAT _C

GROSSMA

SSkg

0 10 20 40 5030 20 10 30

2400

2300

2200

2100

2000

1900

1800

1700

1600

2600

2500

2700

2800

EC135P2S1532_

1SF

40

2900

3000

12000 FT

MIN.

OAT

MAX.

OAT


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GENERALDATA

9.1-1 41/(9.1-1 42 blank)

EASA APPROVED

Rev. 6

A.6. MASS AND BALANCE

No change in the basic Flight Manual data.

A.7. SYSTEMS DESCRIPTION


A.8. HANDLING, SERVICING AND MAINTENANCE


MANUFACTURERS DATA

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CLEARHELIPORT

9.1-1 43

EASA APPROVED

Rev. 10

B. CLEAR HELIPORT

B.1. GENERAL

This subsection provides information necessary for Category A operations at clear heli-

ports.

B.1.1. DEFINITIONS

Takeoff Decision Point TDP 20 ft/30 KIAS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Landing Decision Point LDP 80 ft/40 KIAS/. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

300pR/D< 500 ft/min

B.2. LIMITATIONS (IN ADDITION TO THE LIMITATIONS GIVEN IN PART A, GENERAL)

B.2.1. CERTIFICATION CRITERIA

The definitions given below are related to the respective emergency and normal proce-

dures :

Clear heliport: A surface level heliport, certified for day and night operations, with

minimum field size of a minimum field length defined by the takeoff and landing dis-

tances of this chapter and a minimum field width of 15 m.

B.2.2. MASS LIMITATIONS

For maximum vertical takeoff and landing gross mass refer to Fig. B1 or, if Sandfilter is

installed to Fig. B2 or, if IBF System is installed to Fig. B3. However if external mounted

optional equipment (shown below) is installed, proceed as follows:

All results obtained from maximum takeoff and landing gross mass chart (Fig. B1 or Fig.

B2 or Fig. B3) are to be corrected using these correction values.

Emergency Floatation System on Normal Landing Gear (FMS 9.2-67) subtract 25 kg

Emergency Floatation System on Intermediate Landing Gear

(FMS 9.2-67 and 9.294) subtract 35 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SX 16 Search Light (Front) (FMS 9.213) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . .

SX 16 Search Light (Side) (FMS 9.252) subtract 45 kg. . . . . . . . . . . . . . . . . . . . . . . . .

External Loudspeaker (FMS 9.2-18) subtract 50 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR (IRENCO) (FMS 9.2-45) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR (WESCAM) (FMS 9.2-10) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR Mx15i (FMS 9.2-89) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLIR Ultraforce LEO II (FMS 9.2-72) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . FLIR LEOIIIHD (FMS 9.2-101) subtract 20 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

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CLEARHELIPORT

9.1-1 44

EASA APPROVED

Rev. 11

FLIR Star Safire HD System (FMS 9.2-92) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . .

EOS Star Safire 380-HD (FMS 9.2-106) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . .

External Hoist System (FMS 9.2-20) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

Modified Access Panel 505 1) (FMS 9.2-19 and 9.247) subtract 20 kg. . . . . . . . . . . . .

Cargo Hook 2)(FMS 9.2-19 and 9.247) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . .

Cargo Hook and LH External Mirror Assy 2) (FMS 9.2-19 and 9.247) subtract 50 kg

Cargo Hook and RH External Mirror Assy 2) (FMS 9.2-19 and 9.247) subtract 50 kg

Cargo Hook and both External Mirror Assy 2)(FMS 9.2-19 and 9.247) subtract 75 kg

Snow Skids on High Landing Gear (FMS 9.2-41 and 9.222) subtract 25 kg. . . . . . . .

Snow Skids on Intermediate Landing Gear (FMS 9.2-41 and 9.294) subtract 20 kg.

HELLAS System (FMS 9.2-68) subtract 30 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HF 9000 (FMS 9.2-90) subtract 25 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

EVS 1500 (FMS 9.2-96) subtract 10 kg. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

4 Additional LED Landing lights (FMS 9.2-97) subtract 30 kg. . . . . . . . . . . . . . . . . . . . .



If the ambient conditions (PA, OAT) are presented by a point located in the dashed area

of the diagram (extrapolated beyond the upper gross mass limit), the correction value(s)

may be subtracted from the gross mass value corresponding to that point.

However, the result must not exceed the upper gross mass limit of 2910 kg (2720

kg above 12000 ft PA and 2835 kg above 10000 ft PA )!

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CLEARHELIPORT

9.1-1 45

EASA APPROVED

Rev. 10

Intentionally left blank!

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CLEARHELIPORT

9.1-1 46

EASA APPROVED

Rev. 10

EXAMPLE: For helicopter with external optional equipment installed (see Fig. B1)

Determine: Maximum takeoff and landing gross mass

Known: OAT 22 _C. . . . . . . . . . . . . . . . . . . . . . . .


External Optional Equipment External Loudspeaker (50 kg). . . . . .




3. Move horizontally left and read max. gross mass (2785 kg)

4. Apply correction values for external optional equipment (50 kg) as follows:2785 kg 50 kg = 2735 kg

EXAMPLE: For helicopter with external optional equipment installed (see Fig. B1)

Determine: Maximum takeoff and landing gross mass

Known: OAT 3_C. . . . . . . . . . . . . . . . . . . . . .

Pressure altitude 7000 ft. . . . . . . . . . .

Ext. Optional Equipment SX - 16 (nose mounted) 30 kg. . . .




3. Move horizontally left and read max. gross mass (2860 kg)

4. Apply correction values for external optional equipment (30 kg) as follows:

2860 kg 30 kg = 2830 kg

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CLEARHELIPORT

9.1-1 47

EASA APPROVED

Rev. 10

CATEGORY A (CLEAR HELIPORT) MAXIMUM TAKEOFF AND

LANDING GROSS MASSSKID HEIGHT 4 FT BLEED AIR: OFF

Fig. B1 Maximum Takeoff and Landing Gross Mass

OAT _C

GROSSMASSkg

0 10 20 40 5030 20 10 30

2400

2300

2200

2100

2000

1900

1800

1700

1600

2600

2500

2700

2800

EC135P2S1523_

1

40

2900

3000

Note: altitude lines refer to takeoff/landing pressure altitudes

MIN.OAT

MAX.OAT


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CLEARHELIPORT

9.1-1 48

EASA APPROVED

Rev. 10


LANDING GROSS MASS SANDFILTER INSTALLEDSKID HEIGHT 4 FT BLEED AIR: OFF

Fig. B2 Maximum Takeoff and Landing Gross Mass sandfilter installed

OAT _C

GROSSMA

SSkg

0 10 20 40 5030 20 10 30

2400

2300

2200

2100

2000

1900

1800

1700

1600

2600

2500

2700

2800

EC135P2S1523_

1SF

40

2900

3000


MIN.OAT

MAX.OAT

12000 FT



(see para. A.2.6)

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CLEARHELIPORT

9.1-1 49

EASA APPROVED

Rev. 10


LANDING GROSS MASS IBF SYSTEM INSTALLEDSKID HEIGHT 4 FT BLEED AIR: OFF

Fig. B3 Maximum Takeoff and Landing Gross Mass IBF System installed

OAT _C

GROSSMA

SSkg

0 10 20 40 5030 20 10 30

2400

2300

2200

2100

2000

1900

1800

1700

1600

2600

2500

2700

2800

EC135P2S1523_

1BFe

40

2900

3000


MIN.OAT

MAX.OAT


Observe temperature limitationISA+35_C (max. +45_C) if IBF System installed

(see para. A.2.6)

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CLEARHELIPORT

9.1-1 50

EASA APPROVED

Rev. 10

B.3. EMERGENCY AND MALFUNCTION PROCEDURES

B.3.1. ONE ENGINE INOPERATIVE PRIOR TO TDP

Procedure

1. Collective lever Adjust to OEI-limits or below,

(NR97% 103%)

2. Ground speed Reduce

Prior to touchdown

3. Landing attitude Establish

4. Collective lever Raise as necessary to stop

descent and cushion landing

After touchdown

5. Collective lever Lower slowly

6. Cyclic stick Neutral position

NOTE Observe mast moment limits

7. Engines shutdown Perform

Fig. B4 OEI Rejected Takeoff Profile Clear Heliport

TDP30 KIAS

20 ft HEIGHT

ONE ENGINE INOPERATIVEPRIOR TO TDP

REDUCE GROUND SPEED

30 SEC. POWER RATING

REJECTED TAKEOFF DISTANCE(UNTIL COMPLETE STOP)

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CLEARHELIPORT

9.1-1 51

EASA APPROVED

Rev. 10

B.3.2. ONE ENGINE INOPERATIVE AFTER TDP

Procedure

1. Collective lever Adjust to 30 sec. power, (NR97% 103%)

2. Speed Accelerate to VTOSS(40 KIAS)

3. Climb Initiate with VTOSS

After positive climb is established, but not longer than 30 sec:

4. 2 min. power Select

5. Collective lever Adjust to NR97% 103%

6. Upon reaching 200 ft AGL Accelerate to VY(65 KIAS) and

check deactivation of High NR

mode.

7. Collective lever Adjust to OEI MCP

8. Climb Continue with VYto 1000 ft AGL

9. Single engine emergency shutdown Perform

ONE ENGINE INOPERATIVEAFTER TDP

30 SEC./2.0 MIN. POWER RATING

CLIMB WITHVTOSS

ACCELERATE TO

VTOSS= 40 KIAS

CONTINUED TAKEOFF DISTANCE(35 ft HEIGHT + VTOSS+ POS. CLIMB GRADIENT)

Fig. B5 OEI Continued Takeoff Profile Clear Heliport

35 ft

TDP30 KIAS

20 ft HEIGHT

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B.3.3. ONE ENGINE INOPERATIVE PRIOR TO LDP

NOTE The pilot may elect to balk the landing or to continue the approach. If the deci-

sion is to continue the approach use the procedures for SINGLE ENGINE

FAILURE AFTER LDP. When commencing landing bleed air consumers must

be off.

The following procedures are to be used if the decision is to balk the landing:

Procedure

1. Collective lever Adjust to 30 sec. power or be-

low (NR97% 103%)

2. Climb Initiate with VTOSS

After positive climb is established, but not longer than 30 sec:

3. 2 min. power Select

4. Collective lever Adjust to NR97% 103%

5. Upon reaching 200 ft AGL Accelerate to VY(65 KIAS) and

check deactivation of High NR

mode.

6. Collective lever Adjust to OEI MCP

7. Climb Continue with VYto 1000 ft AGL

8. Single engine emergency shutdown Perform

NOTE The minimum ground clearance is 35 ft.

LDP40 KIAS

80 ft AGL

300p

R/D< 500 ft/min

CLIMB WITHVTOSS

Fig. B6 OEI Balked Landing Profile Clear Heliport

ONE ENGINE INOPERATIVEPRIOR TO LDP

30 SEC./2.0 MIN. POWER RATING

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B.3.4. ONE ENGINE INOPERATIVE AFTER LDP

Procedure

1. Collective lever Adjust to OEI-limits or below

(NR97% 103%)

2. Ground speed Reduce

Prior to touchdown

3. Landing attitude Establish

4. Collective lever Raise as necessary to stop

descent and cushion landing

After touchdown

5. Collective lever Lower slowly

6. Cyclic stick Neutral position

NOTE Observe mast moment limits

7. Engines shutdown Perform

Fig. B7 OEI Landing Profile Clear Heliport

ONE ENGINE INOPERATIVEAFTER LDP

30 SEC. POWER RATING

CAT A LANDING DISTANCE(UNTIL COMPLETE STOP)

REDUCE GROUND SPEED

LDP40 KIAS

80 ft AGL

300pR/D< 500 ft/min

50 ft

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B.4. NORMAL PROCEDURES

B.4.1. TAKEOFF

B.4.1.1. Standard type takeoff flight path

Fig. B8 Standard Type Takeoff Flight Path Profile Clear Heliport

TAKEOFF POWER

HIGE AT 4 ftSKID HEIGHT

TDP30 KIAS

20 ft HEIGHT

ACCELERATE TOVTOSS= 40 KIAS

CLIMB WITH VY

30 KIAS

INCREASE POWERSMOOTHLY (plus

10% torque)

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B.4.1.2. Standard type takeoff procedure

Procedure

1. Pre-takeoff procedure Perform in accordance with Sec-

tion 4 of basic FLM, check HIGH

NR mode selected

2. Radar altimeter TEST; set the bug to 20 ft (TDP

height)

3. Hover 4 ft skid height

4. All instruments Normal operating ranges, note

torque indication

5. Acceleration and climb Start nose down pitch rotation

and simultaneously increase

power smoothly (use hover pow-

er plus 10% torque, without

exceeding TOP) for accelera-

tion. Adjust pitch attitude at

about 25 KIAS to achieve 30

KIAS at 20 ft height.

6. After reaching TDP Apply AEO takeoff power and

accelerate to VY.

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B.4.2. LANDING

B.4.2.1. Standard type landing flight path profile

Fig. B9 Standard Type Landing Flight Path Profile Clear Heliport

POWER AS REQUIRED

LDP

40 KIAS80 ft AGL

300pR/D< 500 ft/min

REDUCE RATE OF DESCENT

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B.4.2.2. Standard type landing flight path procedure

Procedure

1. Pre-landing procedure Perform

2. Radar altimeter bug Set to LDP height (80 ft)

3. Landing Initiate to arrive at LDP with a

speed of 40 KIAS and a rate of

descent of 300pR/D< 500 ft/min.

4. After reaching LDP Adjust collective pitch to main-

tain desired rate of descent, andto terminate approach.

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B.5. PERFORMANCE DATA

B.5.1. TAKEOFF PERFORMANCE

B.5.1.1. Assured Minimum Flight Conditions

POWER SPEED R/C ALTITUDE

HIGE T/O (AEO) 0 0 4 ft skid height

CLIMB 2.0 min (OEI) VTOSS= 40 KIAS 100ft/min 200 ft AGL

CLIMB MCP (OEI) VY = 65 KIAS 150 ft/min 1000 ft AGL

B.5.1.2. Takeoff distance required

The takeoff distance charts show the wind-corrected rejected takeoff distances required

(Fig. B10) and continued takeoff distance required (Fig. B11). The flight planning has to

be based on the rejected andcontinued takeoff distance chart andthe respective chart

for segment I and II flight path (Figs A4 A15).

EXAMPLE: (see Fig. B10)

Determine: Rejected takeoff distance required

Known: OAT 35 _C. . . . . . . . . . . . . . . . . . . . . . . .


Solution: Rejected takeoff distance = 370 meters

1. Enter chart at known OAT (35_C).

2. Move vertically upwards to the known pressure altitude (5500ft).

3. Move horizontally right to the guideline of the right graph.

4. From intersection move downwards and readrejected takeoff distance = 370 m

EXAMPLE: (see Fig. B11)Determine: Continued takeoff distance required

Known: OAT 35 _C. . . . . . . . . . . . . . . . . . . . . . . .


Solution: Continued takeoff distance = 290 meters


2. Move vertically upwards to the known pressure altitude (5500ft).


4. From intersection move downwards and readcontinued takeoff distance = 290 m
http://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildoc

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CATEGORY A (CLEAR HELIPORT)

CONTINUED TAKEOFF DISTANCE REQUIRED1 X PRATT & WHITNEY PW 206 B2

NOTE HELICOPTER CONFIGURATION MUST COMPLY WITH THE MASS-ALTITUDE OAT LIMITS,

AS SHOWN IN FIGURE B1 OR B2 FOR THIS DIAGRAM TO BE VALID.

Fig. B11 Continued Takeoff Distance Required


(see para. A.2.6)

Observe temperature limitationISA+35_C (max. +45_C) if IBF System installed

(see para. A.2.6)

CTOD_F

LM_

T/P2_

clear

XC/DLinke

05/03

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B.5.1.3. OEI Climbout Flight Path

The takeoff flight path (Fig. B13) begins at the end of the continued takeoff distance re-

quired or balked landing, at 35 feet above the takeoff surface or higher and V toss, and is

divided into two segments.

Climbout flight path segments I and II (Figs A4 to A15)

Climbout segment I diagrams (Fig. A4 to A9) provide data for 35 ft to 200 ft AGL at 2min

power (acceleration from Vtossto VY).

Climbout segment II diagrams (Fig. A10 to A15) provide data for 200 ft to 1000 ft AGL at

MCP and VY.

Both chart types show the height gain over a horizontal distance of 100 ft.

The distance required for horizontal acceleration from Vtossto VYis provided in Fig. B12.

EXAMPLE: (see Fig. B12)

Known: OAT 35 _C. . . . . . . . . . . . . . . . . . . . . . . .


Headwind 40 kt

for calculation 50%: 20 kt. . . . . . . . . . .

Solution: Distance required for horizontal acceleration from Vtossto VY= 465 m


2. Move vertically upwards to known pressure altitude (5500 ft).


4. From intersection of headwind (20kt) move downwards and readacceleration distance = 465 m
http://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildochttp://d/desktop.ileaf/ILeaf_Zivil_Library.ilcab$/ec135.ilcab/flieg.ildrw/flmEC135.ildrw/P2__.ildrw/Sups-P2__CPDS_.ilcab/NewSUPs_neu.ilboo/9.1-1R10_.ildrw/9.1-1R10_.ilboo/General__A__R10_.ildoc

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