FLIGHT MANUAL BK117 B-1 - Regulations.gov...FLIGHT MANUAL BK117 B-1 0 - 11 EASA APPROVED Rev. 21 LIST OF EFFECTIVE PAGES NOTE N, R, or D indicate pages which are New, Revised or Deleted

FLIGHT MANUAL BK117 B-1

0 - 5EASA APPROVEDRev. 21

LOG OF REVISIONS

FIRST ISSUE

ORIGINAL 0 DEC 10, 1987

REVISION 1 APR 08, 1988

REVISION 2 MAY 20, 1988


REVISION 4 FEB 13, 1991

REVISION 5 MAR 17, 1992

REVISION 6 MAY 07, 1992

REVISION 7 MAR 11, 1993

REVISION 8 JUL 08, 1993

REVISION 8A MAR 23, 1995

REVISION 9 JUL 25, 1996

REVISION 9A JAN 30, 1998


REVISION 11 MAY 18, 2005EASA approval no.: 2005-4260

REVISION 12 OCT 11, 2005EASA approval no.: R.C.01230

REVISION 12.1 JAN 29, 2006

REVISION 13 JAN 30, 2006EASA approval no.: R.A.01072

REVISION 14 JUL 24, 2006EASA APPROVAL NO.: R.A.01152

REVISION 14.1 OCT 17, 2006

REVISION 14.2 DEC 01, 2006

REVISION 14.3 APR 27, 2007

REVISION 15 JAN 11, 2008EASA approval no.: R.A.01429

REVISION 16 AUG 14, 2008EASA approval no.: R.A.01495

REVISION 17 OCT 07, 2009EASA approval no.: 10027515

REVISION 18 MAY 17, 2010EASA approval no.: 10030041

REVISION 19 JUL 19, 2012EASA approval no.: 10040648

REVISION 20 MAR 26, 2013EASA approval no.: 10044212

REVISION 20.1 MAR 25, 2015

REVISION 21 (see entry below)

REVISION 21 Approved by EASA

Date: NOV 26, 2015 EASA approval no.: 10055659

FLIGHT MANUAL BK117 B–1

0 - 6EASA APPROVED

Rev. 21

LOG OF REVISIONS (CONTINUED)


0 - 11EASA APPROVED

Rev. 21

LIST OF EFFECTIVE PAGES

NOTE N, R, or D indicate 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 Remove and dis-pose of superseded pages, insert the latest revision pages and complete the Record of Revi-sions as necessary.

Page RevNo. Remarks/Effectivity

Section 0

0-1 9 Cover Sheet (TITLE)

0-2 14 Approving Authorities

A 10 DGAC only

B 10 DGAC only

C 10 DGAC only

0-3/0-4 9 Manual Contents

R 0-5 21 Log of Revisions

R 0-6 21 Log of Revisions

0-7 0 Record of Revisions

0-8 0 Record of Revisions

0-9 0 Record of temp. Rev.

0-10 0 Record of temp. Rev.

R 0-11 21 List of effective pages








R 0-18A 21 List of effective pages

R 0-18B 21 List of effective pages

R 0-18C/(D blank)

21 List of effective pages

0-19/0-20 8 Record of modifications

ROIV – Record of SW versionsand performed(A)SBs

ROOT – Record of used oil types

Section 1

1-i 11

1-ii 11


1-1 11

1-2 11

1-3 11

1-4 11

1-5

1-6

11

11

1-7 11

1-8 11

1-9 11

1-10 11

1-11 11

1-12 11

1-13 11

1-14 11

1-15

1-16

11

11

1-17 11

1-18 11

1-19 11

1-20 11

1-21 11

1-22 11

Section 2

2-1 7

2-2 8

2-3 7

2-4 10

2-5 8

2-6 0

R 2-7 18

N 2-7-a 18

N 2-7-b 18


0 - 12EASA APPROVED

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R 2-8 18 Not for DGAC

R 2-8 18 DGAC only

2-9 8

2-10 3

2-11 0

2-12 0

2-13 0

2-14 3

2-15 8 Not for DGAC

2-15 8 DGAC only

2-16 5

2-17 19

2-18 19

2-19 12

2-20 12

2-21 0

2-22 8

2-23 9

2-24 92-25 9 Not for Argent. and

Brazil. reg. helicopters2-25 9 Brazilian registered

helicopters only2-25 9 Argentinian registered

helicopters only2-26 9

2-27 10

2-28 9

2-29 9

2-30 9

2-31/2-32 9Section 3

3-i 10 S/N v 7183

3-i 10 S/N w 7184

3-ii 14

3-iii/3-iv 20.1 S/N v 7183

3-iii/3-iv 20.1 S/N w 7184

3-1 8A

3-2 10

3-3 19

3-4 8A


3-5 8A S/N v 7183

3-5 8A S/N w 7184

3-6 10

3-7 8A

3-8 8A

3-9 8A S/N v 7183

3-9 8A S/N w 7184

3-10 8A

3-11 19

3-12 8A

3-13 8A S/N v 7183

3-13 8A S/N w 7184

3-14 8A S/N v 7183

3-14 8A S/N w 7184

3-15 8A If YAW CSAS installed

3-16 8A

3-17 8A

3-18 10

3-19 10

3-20 8A

3-21 17

3-22 8A

3-23 17

3-24 8A

3-25 20.1

3-26 20.13-27 20.1 S/N v 71833-27 20.1 S/N w 7184

3-28 20.1

3-29 8A

3-30 8A

3-31 8A

3-32 8A

3-33 8A

3-34 8A

3-35 8A

3-36 8A

3-37 14

3-38 14


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3-45 14

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3-51 14

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3-53 14

3-54 14 S/N v 7183

3-54 14 S/N w 7184

3-55 14 S/N v 7183

3-55 14 S/N w 7184

3-56 14

3-57 14 S/N v 7183

3-57 14 S/N w 7184

3-58 14

3-59 14

3-60 14

3-61 20.1

3-62 20.1 S/N v 7183

3-62 20.1 S/N w 7184

3-63 20.1 S/N v 7183

3-63 20.1 S/N w 71843-64 20.1 If LEAR SIEGLER trim

actautors installed3-64 20.1 If SFENA trim actau-

tors installed3-65 20.1

3-66 20.1

3-67 20.1

3-68 20.1 If YAW CSAS installed

Section 4

4-1/4-2 4


4-3/4-4 4

4-5/4-6 0

4-7 34-8 2 S/N v 71834-8 2 S/N w 71844-9 20.1 S/N v 7183

4-9 20.1 S/N w 7184

4-10 20.1

4-11 0

4-12 0

4-13 0

4-14 0

4-15 20.1

4-16 20.1

4-17 7 S/N v 7183

4-17 7 S/N w 7184

4-18 2 S/N v 7183

4-18 2 S/N w 71844-19 17 (See respective page)4-19 17 (See respective page)

4-20 17

4-21 17

4-22 17 S/N v 7183

4-22 17 S/N w 7184

4-23 7

4-24 7

4-25 5 If YAW CSAS installed

4-26 6

4-26A 9 (See respective page)

4-27 174-28 17 S/N v 71834-28 17 S/N w 7184

Section 5

5-i 9

5-ii 9

5-iii/5-iv 9

5-1 9

5-2 9

5-3 9

5-4 9


0 - 14EASA APPROVED

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5-5 9

5-6 9

5-7 9

5-8 9

5-9 9

5-10 9

5-11 9

5-12 9

5-13 0

5-14 0

5-15 0

5-16 0

5-17 0

5-18 0

5-19 0

5-20 0

5-21 0

5-22 0

5-23/5-24 0

5-25 8

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5-49 8

5-50 8

5-51 8

5-52 8

5-53 8

5-54 8

5-55 8

5-56 8

5-57/5-58 8

Section 6

6-1/6-2 0

6-3 0

6-4 0

6-5/6-6 0

6-7 7

6-8 0

6-9 0

6-10 7

6-11 7

6-12 0

6-13 0

6-14 0

Form MBR-1 0

Form MBR-1 0

Form MBR-1 0

Form MBR-1 0

Form MBR-1 0

Form EL-1 0

Form EL-1 0

Form EL-1 0

Form EL-1 0

Form EL-1 0

Section 7

7-1/7-2 0


0 - 15EASA APPROVED

Rev. 21


Section 8

8-1/8-2 0

Section 9

9-i 12.1

9-ii 12.1

9-1 9

9-2 9

9-3 9

9-4 9

9-5 9

9-6 9

9-7 9

9-8 9

9-9 9

9-10 9

9-11 9

9-12 9

9-13 9

9-14 9

9-15 9

9-16 9

9-17 12.1

9-18 12.1

Section 10

10-1 15 Log of Supplements








10-9/10-10 15 Log of Supplements

10-2-1 9

10-2-2 20

10-2-3 9A

10-2-4 20

10-2-5 20


10-2-6 20

10-2-7 20

10-2-8 20

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10-3-1 0

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10-3-11 0

10-3-12 0

10-3-13 0

10-4-1 0

10-4-2 0

10-4-3 5

10-4-4 0

10-4-5 0

10-5-1 0

10-5-2 0

10-5-3 0

10-5-4 0

10-6-1 4

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10-7-1 0

10-7-2 0


0 - 16EASA APPROVED

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10-8-2 8

10-8-3 0

10-8-4 0

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10-8-6 0

10-9-1 0

10-9-2 0

10-10–1 0

10-10-2 0

10-11-1 3

10-11-2 3

10-11-3 3

10-11-4 3

10-11-5 3

10-11-6 8

10-11-7 3

10-11-8 3

10-11-9 3

10-11-10 3

10-12-1 9

10-12-2 9

10-12-3/-4 9

10-13-1 0

10-13-2 0

10-15-1 5

10-15-2 5

10-15-3 5

10-15-4 5

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10-15-6 5

10-16-1 0

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10-17-1 0

10-17-2 0


10-17-3 0

10-17-4 0

10-17-5 0

10-18-1 0

10-18-2 5

10-18-3 0

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10-20-1 0

10-20-2 0

10-20-3 0

10-20-4 0

10-21-1 0

10-21-2 0

10-21-3 0

10-22-1 0

10-22-2 0

10-23-1 0

10-23-2 5

10-23-3 8

10-23-4 5

10-23-5 3

10-23-6 0

10-23-7 0

10-25-1 0

10-25-2 0

10-25-3 0

10-26-1 0

10-26-2 0

10-26-3 0

10-26-4 0

10-26-5 0

10-26-6 0

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0 - 17EASA APPROVED

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10-31-1 0

10-31-2 0

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10-32-1 18

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10-32-7 18

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10-33-1 0

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10-33-3 0

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10-33-5 0

10-34-1 0

10-34-2 5

10-34-3 7

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10-35-1 20.1

10-35-2 20.1

10-35-3 20.1

10-35-4 20.1

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10-35-6 20.1

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10-35-8 20.1

10-35-9 20.1

10-35-10 20.1

10-35-11 20.1

10-35-12 20.1

10-35-13 20.1

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10-35-21 20.1

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0 - 18EASA APPROVED

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10-41-2 2

10-41-3 0

10-41-4 5

10-41-5 0

10-41-6 0

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10-41-8 0

10-41-9 0

10-41-10 0

10-42-1 0

10-42-2 0

10-42-3 0

10-42-4 0

10-42-5 0

10-42-6 0

10-44-1 0

10-44-2 0

10-44-3 0

10-45-1 7

10-45-2 7

10-45-3 7

10-45-4 7

10-46-1 4

10-46-2 5

10-46-3 4


10-46-4 4

10-46-5 4

10-46-6 4

10-46-7 3

10-46-8 4

10-47-1 0

10-47-2 5

10-47-3 0

10-47-4 0

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10-47-7 0

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10-48-1 3

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0 - 18AEASA APPROVED

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10-48-27 3

10-48-28 3

10-48-29 3

10-48-30 3

10-48-31 3

10-48-32 3

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10-48-35 3

10-48-36 3

10-48-37 3

10-48-38 3

10-48-39 3

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10-48-42 3

10-48-43 3

10-48-44 3

10-48-45 3

10-48-46 3

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10-48-49 3

10-48-50 3

10-53-1 3

10-53-2 3

10-53-3 3

10-53-4 3

10-53-5 3

10-53-6 3

10-53-7 3

10-53-8 3

10-53-9 3

10-53-10 3

10-53-11 3

10-53-12 3

10-57-1 15

10-57-2 15


10-57-3 15

10-57-4 15

10-58-1 4

10-58-2 4

10-58-3 4

10-58-4 4

10-58-5 4

10-58-6 8

10-58-7 4

10-58-8 4

10-58-9 4

10-58-10 4

10-58-11 4

10-59-1 5

10-59-2 5

10-59-3 5

10-59-4 5

10-59-5 5

10-59-6 5

10-59-7 5

10-60-1 5

10-60-2 5

10-60-3 5

10-60-4 8

10-60-5 5

10-63-1 8A

10-63-2 8A

10-63-3 4 S/N v 7183

10-63-3 4 S/N w 7184

10-63-4 4

10-63-5 4

10-63-6 4

10-63-7 4

10-63-8 4

10-66-1 7

10-66-2 7

10-66-3 7

10-66-4 7

10-66-5 7


0 - 18BEASA APPROVED

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10-66-6 9

10-66-7 7

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10-66-21 7

10-66-22 7

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10-66-26 7

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10-67-1 7

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10-69-7 9

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10-69-10 9

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10-69-12 9

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10-71-1 9

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10-71-3 9

10-71-4 9

10-71-5 9

10-71-6 9

10-74-1 13

10-74-2 13

10-74-3/4 13

Section 11

1 / (2 blank) 9 Log of Supplements

11-1-1/-2 3

11-1-3 8

11-1-4 3

11-1-5/-6 8

11-1-7 3

11-1-8 3

11-1-9/-10 3

11-1-11 8

11-1-12 3

11-1-13 3

11-1-14 8

11-1-14A 8

11-1-14B 8

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11-1-21/-22 3

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11-1-37 8

11-1-38 8

11-1-39/-40 8

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11-1-42 8

11-1-43/-44 8

11-2-1 16

11-2-2 16

11-2-3 16

11-2-4 16

11-2-5 16 S/N v 7183

11-2-5 16 S/N w 7184

11-2-6 16

11-2-7 16

11-2-8 16

11-3-1 0

11-3-2 5

11-3-3 0

11-3-4 0

11-5-1 16 S/N w 7184

11-5-2 16 S/N w 7184

11-5-3 16 S/N w 7184

11-5-4 16 S/N w 7184


11-5-5 16 S/N w 7184

11-5-6 16 S/N w 7184

11-5-7 16 S/N w 7184

11-5-8 16 S/N w 7184

11-5-9 16 S/N w 7184

11-5-10 16 S/N w 7184

11-5-11 16 S/N w 7184

11-5-12 16 S/N w 7184

11-6-1 16 S/N v 7183

11-6-2 16 S/N v 7183

11-6-3 16 S/N v 7183

11-6-4 16 S/N v 7183

11-6-5 16 S/N v 7183

11-6-6 16 S/N v 7183

11-6-7 16 S/N v 7183

11-6-8 16 S/N v 7183

11-6-9 16 S/N v 7183

11-6-10 16 S/N v 7183

11-6-11/-12 16 S/N v 7183

MBB HELICOPTERSFLIGHT MANUAL MBB - BK 117 B-1

SEC T ION 4

NORMAL PROCEDURES

Table of Contents

4. NORMAL PROCEDURES .4- 3

4.1

4.2

4.2.14.2.24.2.3

4.3

Introduction . .

Preparation for i

Flight restrictionsFlight planningMass and balance

Preflight check.

.4- 3

.4- 3

.. 4 - 3.4- 3

· ... 4 - 3

.4- 5

4.3.14.3.24.3.3

GeneralExterior checkInterior check

.4- 5

.4- 7· 4 - 17

4.4

4.4.14.4.24.4.34.4.4

Starti engines

Before starting engines. . .Starting first engine .Starti ng second engi ne . . . .Cold weather start

· 4 - 20

· 4 - 20· 4 - 20

· 4 - 22· 4 - 23

Pre-takeoff check

Tal(eoff check.

Pre-landlng chec~

4 - 27

4 - 27

4 - 28

· 4 - 24

· 4 - 244 - 25

· 4 - 26· 4 - 26

.. 4 - 26· 4 - 26· 4 - 26

4 - 26A4 - 26A I

4 - 27

of engines

Hydraul i c system check . . . .YAH CSAS system check .SPAS check . . . . .Avionic checksMiscellaneous checksPower check ..... . . . .Bleed air heating check ....Force Trim Release (FTR) function check (EFFECTIVITY) .Engine overspeed trip system check (EFFECTIVITY) ..

Shut

System checks . . . . . .

4.8

4.9

4.5

4.5.14.5.24.5.34.5.44.5.54.5.64.5.74.5.84.5.9

4.6

4.7

Page 4 - 1 / 4 - 2Rev. 4

LBA approved

LB25.1

MBB HELICOPTERSFLIGHT MANUAL MBB - BK 117 B-1

4. NORMAL PROCEDURES

4.1 Introduction

This section contains instructions and recommended procedures thatare peculiar to the operation of this helicopter.For definition of terms, abbreviations and symbols used in this section refer to section 1.

4.2 Preparation for flight

4.2.1 Flight restrictions

The minimum, normal, maximum and cautionary operation ranges forthe helicopter and its subsystems are indicated by instrument markings, placards and decals.

For a description of helicopter and subsystem restrictions refer tosection 2, Limitations.

Before helicopter operation with a passenger on copilotlsseat, cyclic stick and collective pitch lever on copilot1sside should be removed, copilot's pedals adjusted to themost forward position and the dual control covers (see FMS10-16) installed.If the covers are not at hand, cyclic and collective leversshall remain installed. However, in this case, the passengermust be briefed properly before engine start-up not to interfere with any pilot's control operation.

4.2.2

4.2.3

Flight planning

Refer to sections 5 and 9 to determine required fuel, airspeed andpower settings for takeoff, climb, cruising, hovering and landingdata necessary to complete the mission.

Mass and balance

The takeoff and anticipated landing gross mass and balance should beobtained before takeoff and checked against mass and load limits,center of gravity and height-velocity limitations, section 2.

LB25.2

Page 4 - 3 / 4 - 4Rev. 4

LBA approved

---------- MBB HELICOPTERS ---------FLIGHT MANUAL MBB - BK 117 B-1

4. 3 Preflight check

4.3.1 General

The preflight check shall be accomplished according to Flight Manual, Maintenance Manual or Pilot's Checklist.

The preflight check is not a detailed mechanical inspection, butessentially a visual check of the helicopter for correct condition e

This check shall be accomplished before each fli%ht. Items without an asterisk * need to be checked only once efore the firstflight of ,the day G

When unusual local conditions dictate, the extent and frequencyof this check shall be increased to promote safe operation.

The following list contains only check items for thestandard configuration.

In addition to these items, check antennas and allinstalled optional equipment and make certain thatrelevant intermediate and special inspections according to Maintenance Manual are complied with e

For optional equipment check items refer to therespective Flight Manual Supplements or MaintenanceManual, chapter 8000

(LB1210-A-3)

Page 4 - 5 /4 - 6Rev. 0

LBA approved

------------ MBB HELl COPTERS -----------FLIGHT MANUAL MBB - BK 117 B-1

The exterior check is laid out as a waf karound check, starting forward right at pilots door I proceed clockwise to the tail boom f tothe left-hand-side (including the upper and lower areas of the helicopter) and being completed at the nose area of the helicopter ..

1 Fuselage2 Cabin3 Tail boom4 Fuselage5 Cabin

Right sideTopAft areaLeft sideFront

The area around the helicopter should be clear of allforeign objects ..

If possible r ensure that the helicopter is headed intothe wind before starting the engines ..

To avoid excessive drain on the helicopter battery,particularly during cold weather, all ground operationsshould be conducted using the external power unit(EPU) ..When the battery is used, the operation of electricalequipment should be kept to a minimum ..

I

(LB1210-A-4)

Page 4 - 7Rev. 3

LBA approved

------------ MBB HELl COPTERS ----------FLIGHT MANUAL MBB .... BK 117 B-1

I Up to SiN 7183

Before exterior check (continued)

*

***

Helicopter forms anddocuments

Fuel tanks

Fuselage underside

Covers and tie downs

Ice and snow (if any)

Ground handling wheels

Center control panel

All switches and avionicsexcept:

FUEL VALVE I + 11

Collective pitch

All switches

Overhead panel

All circuit breakers

All switches

Power levers

I nstrument panel

FI RE EXT switches

AGENT DISCH switch

FIRE DET TEST switch

All switches and avionics


MASTER PWR switch

Voltmeter indication

PWR SELECT switch

Check, complete

Drain

Condition, no fuel leaks

Removed

Removed

Removed

OFF

OP I guarded

OFF orposition

In

OFF

OFF

RM

OFF

NORM

OFF

NORM

Minimum 24 V DC

BAT

* To be checked before each flight

Page 4 OD 8Rev .. 2

LBA approved

(LB1210-A-S)

------------- MBB HELICOPTERSFLIGHT MANUAL MBB ... BK 117 B-1

4.3.2

The exterior check is laid out as awal karound check, starting forward right at pllot.'s door! proceeding clockwise to the tail boom! tothe left-hand-side (including the upper and lower areas of the helicopter) and being completed at the nose area of the helicopter"

1 Fuselage2 Cabin3 . Tail boom4 Fuselage5 Cabin

Right sideTopAft areaLeft sideFront

If possible I ensure that the helicopter is headed intothe wind before starting the engines ..

The area around the helicopter should be clear of allforeign objects"

To avoid excessive drain on the helicopter battery!particularly during cold weather I all ground operationsshould be conducted using the external power unit(EPU) .When the battery is used ,the operation of electricalequipment should be kept to a minimum ..

I

( 210-A-4)

Page 4 - 7Rev .. 3

LBA approved

------------ MBB HELICOPTERSFLIGHT MANUAL MBB .... BK 117 B-1

I EFFECTIVDTY SiN 7184 and subsequent

Before exterior check (continued)

* Helicopter forms and .... Check, completedocuments

Fuel tanks - Drain

Fuselage underside - Condition, no fuel leaks

* Covers and tie downs .... Removed

* Ice and snow (if any) .... Removed

* Ground handling wheels .... Removed


II

*


FUEL VALVE I + I1

Collective pitch

All switches

Overhead panel


All switches

Power levers

Instrument panel

FIR E EXT switches

AGENT DISCH switch

Ft RE DET TEST switch



PWR SELECT switch


To be checked before each flight

Page 4 - 8Rev. 2

- OFF

.... GP, guarded

.... OFF orneutral position

.... In

.... OFF

.... OFF

.... NORM

.... OFF

.... NORM

- OFF

- BAT

- Minimum 24 V DC

LBA approved

(LB1210-A-27)


EASA APPROVEDRev. 20.1 4 - 9

EFFECTIVITY Up to S/N 7183

Cockpit (continued)

BUS–TIE switch - NORM

Pitot tube heating (PITOT HTR)

- Function

Static port heating (STATIC HTR)

- Function

Lighting

Position lights - Function

Anti-collision light - Function

Strobe lights - Function

Landing lights - Function

Before night flights

Instrument lights - Function

Utility light - Function

Dome light - Function

Hand lamp - Function

MASTER PWR switch - OFF


EASA APPROVEDRev. 20.14 - 10

Fuselage - right side

Cockpit air intake - Clear

Lower cockpit window - Condition

L Pedal area - No foreign objects

Circuit breakers, fwd junction box - Check in

L Pitot tube - Clear, condition

Drain port - Clear

L Static ports (2) - Clear

Cockpit door - Condition, function

Pilot seat and safety belt - Condition

Cabin door - Condition, function

EFFECTIVITY Jettisonable sliding door installed, after ASB-BK117-20A-114

Stretch seal strips on exterior andinterior jettisoning handles

- Condition

EFFECTIVITY All

Cabin top

Cockpit overhead window - Condition

Hydraulic compartment - No leakage, no foreign objects

Hydraulic system - Condition

Hydraulic system filter cloggingindicator pins (4)

- Check in

L Hydraulic system fluid reservoirs (2) - Oil level

Hydraulic system outboard fittings (4) - Secured

Rotor brake oil reservoir - Oil level, filler cap secured

L Hydraulic compartment cowling - Closed, secured

L Oil cooler air inlet screen (2) - Clear

L Transmission oil - Oil level

L To be checked before each flight



EFFECTIVITY S/N 7184 and subsequent

Cockpit (continued)

BUS–TIE switches (2) - ON

Pitot tube heating (PITOT HTR)

- Function

Static port heating (STATIC HTR)

- Function

Lighting

Position lights - Function

Anti-collision light - Function

Strobe lights - Function

Landing lights - Function

Before night flights

Instrument lights - Function

Utility light - Function

Dome light - Function

Hand lamp - Function

PWR SELECT switch - OFF







Circuit breakers, fwd junction box - Check in


Drain port - Clear



Pilot seat and safety belt - Condition




- Condition

EFFECTIVITY All

Cabin top

Cockpit overhead window - Condition

Hydraulic compartment - No leakage, no foreign objects

Hydraulic system - Condition

Hydraulic system filter cloggingindicator pins (4)

- Check in

L Hydraulic system fluid reservoirs (2) - Oil level

Hydraulic system outboard fittings (4) - Secured

Rotor brake oil reservoir - Oil level, filler cap secured

L Hydraulic compartment cowling - Closed, secured

L Oil cooler air inlet screen (2) - Clear

L Transmission oil - Oil level


---------- MBB HELICOPTERS ---------FLIGHT MANUAL MBB .... BK 117 B-1

Fuselage -- right side (continued)

Swash plate and boot .... Condition

*

*

Main rotor head

Blade attachment bolts,driving link assembly androtor hub cap

Rotating control rods

Rotating control rod.,.spherical bearings

Vibration absorbers

Rotor blades and trimtabs

- Oil level, condition

.... Condition, secured

.... Condition I freemovement

.... Check for smooth operation by moving controlrods by hand

.... Condition I freemovement, noleakage

- Condition, turn rotor by hand indi rection of rotorrotation and checkfor free run

* Maintenance steps

Landing g'ear and step

Vents/drainports

.... Check in

.... Condition

- Clear

*

*

Transmission compartment

Oil cooler· inlet duct

Transmission oil coolerblock plate

Engine oil tank

Eng ine oi I tan k

Transmission

.... No leakage, no foreign objects

.... Clear

.... Installed, when OATbelow -35°C (recommended to be removed,when OAT above+35 QC)

- Oil level

- Condition,no leakage,security of mounting, filler cap secured and locked

- Condition


Page 4 .... 11Rev. 0

LBA approved

(LB1210-A-8)

----------- MBB HELl COPTERS ----------FLIGHT MANUAL MBB - BK 117 B-1

Fuselage aD right side (continued)

Transmission strurs

Transmission filterclogging indicator pin

Transmission oil filler cap

Mixing lever assembly

Rotor brake system

* Transmission access door

Engine compartment

Engine

- Condition, secured

.. Check in

.. Secured, locked

... Condition, secured

- Condition

- Closed, secured

... No leakage,no foreign objects

... Condition

*

**

Engine air inlet screen

Wiring, linkages and lines

Tubes and nozzles of enginewater washing system(if installed)

Engine exhaust pipe

Engine mounts

Fi re detectors

Engine access door

Maintenance step

Battery (if located here)

Battery door

Fire extinguisher bottles

Clear [ secured

... Condition 1

no leakage,no chafing

Security

Condition I secured

... Condition I secured

... Condition

... Closed[ secured

aD Closed[ secured

- Condition, no electrolytespewage, security of mounting

- Closed, secured

- Check for correctpressure indications(2) according to thepressure-temperaturetable


Page 4 ... 12Rev. 0

LBA approved

(LB1210-A-9)

----------- MBB '-HE:LICOPTERS -------.;..-----------FLIGHT MAN-UAL MBB - BK 117'-B-1

Fuselage" right side (continued)

NOTE Engine must be cold for pressure-temperaturetable to be valid.

*. Red bursting "plate forfire extinguisher system

.. Check undamaged

*

Aft engine cowling


Clam shell doors

First aid kit

... Secured

.. Condition

- Condition, function

- On board

Baggage compartment

Small baggage compartment

* Clam shell doors

... Condition

... Condition

.. Closed, secured

* Tail boom - right side ... Condition

* RH horizontal and vertical .. Conditionstabilizer I position light

Vertical fin and cowling .. Condition I secured

Position light and anti- .. Conditioncollision light

Tail skid - Condition

* Tail rotor gear box .. Oil level, noleakage, fillercap secured

NOTE Verification of oil level may be easier when tailskid is shortly shaken. .

Tail rotor head, shaft, bellow ... Condition

* Pitch links

Blade attachment bolts,balance masses,dynamic masses

Sliding sleeve

* Tail rotor blades

- Condition

- Condition,secured

- Check free movement

- Condition

* To be checked before each flight,

Page 4·· - 13Rev. 0

LBA approved

(LB1210-A-10)

---------- MBB HELICOPTERS ---------FLIGHT MANUALMBB ... BK 117 B-1

Tail boom (continued)

Vertical fin and cowling ... Condition I secured

... Filler cap anddrain screw secured

... Oil level,no leakage

Verification of oil level may be easier when tailskid is shortly shaken ..

Intermediate gear box

Intermediate gear box*

* Vertical fin access door - Closed, secured

* LH horizontal and verticalstabilizer, position light

* Tail boom .. left side

... Condition

- Condition

Flux valve cover .. Condition

I-usellaae - side

Aft engine cowling

Bleed air heater screens (2)

.. Secured

.. Clear

Engine compartment

Engine

.. No leakage,no foreign objects

- Condition

* Engine air inlet screen Clear, secured

Wiring, linkages and lines

Tubes and nozzles of enginewater. washing system(if installed)

.. Condition,no leakage,no chafing

- Security

Engine exhaust pipe Condition, secured

Engine mounts ... Condition, secured

Fire detectors - Condition

* Engine access door - Closed, secured

* Transmission compartment - No leakage,no foreiqn objects


Page 4 ;... 14Rev. 0

LBA approved

(LB1210-A-11)



Fuselage - left side (continued)

Oil cooler inlet duct - Clear

Transmission oil cooler block plate - Installed, when OAT below –35 _C (rec-ommended to be removed when OATabove +35 _C)

L Engine oil tank - Oil level

Engine oil tank - Condition, no leakage,security of mounting, filler capsecured and locked

Transmission - Condition

Transmission struts - Condition, secured

Transmission oil filterclogging indicator pin

- Check in

Mixing lever assembly - Condition, secured

Rotor brake system - Condition

L Transmission access door - Closed, secured

L Maintenance step - Closed, secured

Landing gear and step - Condition

L Fuel filler cap - Secured, locked

Vents and drainports - Clear

L Fuselage - left side - Condition




- Condition

EFFECTIVITY All


Cyclic stick - Secured, safety-wired

Copilot seat and safety belts - Condition

L For single pilot flights:Copilot’s safety belts

- Fastened, secured





Fuselage - left side (continued)

Drain port - Clear





Nose area

Cockpit windshields - Condition, clean

Windshield wipers - Condition

OAT-bulb - Condition

Battery - Condition, no electrolyte spillage,security of mounting

Battery connectors (2) - Connected

Avionic equipment - Condition

L Battery/avionics access door - Closed, secured

Circuit breaker for EPU - Check in

L EPU access door - Closed, secured

Battery vents - Clear

Landing light - Condition, retracted

L Fuselage bottom - Condition

Miscellaneous

L Baggage, cargo, loose items - Stowed, secured

Hand-fire extinguisher - On board, check pressure

Hand lamp - On board

L Passengers - Briefed


FLIGHT MANUAL MBB - BK 117 B-1

EFFECTIVITY

4.3.3 *

Up to SIN 7183

Interior check.

Seat and pedals

Safety belts

Shoulder harness locks



- PWR SELECT switch- STATIC PRESS switch- GEN TRIP switch- DG switch- FUEL VALVE I + 11

- Adjust

- Fasten, adjust

- Function

- OFF

- BAT- PRIMARY- NORM- SLAVE- OP, guarded

I

Collective pitch (pilot/copilot>

All switches

Instrument panel

FIRE EXI switches

AGENT DISCH switch

FIRE OET TEST switch


Clock

Overhead panel

All switches

All ci r cul t breakers

Power levers

COLD START switch

HYD TEST switch

OAT

- OFF orneutral position

- NORM

- OFF

- NORM


- Set

OFF

- In

- OFF

- NORM

- NORM

Check

*

LB244.10

To be checked before each. fl i ght

Page 4 - 17Rev. 7

LBA approved

------------- MBB H EL ICOPTERS ------------FLIGHT MANUAL MBB - BK 117 B-1

I EFFIECTBVITV Up toS/N 7183

IPre-start check

MASTER PWR switch


EMER LTS switch

MASTER PWR switch

MASTER PWR switch

EMER LTS switch

EMER LTS switch

PWR SELECT switch

for battery start

for EPU start

BUS-TIE switch

DOMEl..IGHT pushbutton

BUS-TI E switch

BUS-TI E switch

DOME LIGHT pushbutton

FUE.L PUMP PRIME switches

FUEL PUMP PRIME switches

FUEL PUMP XFER switches


Page 4 - 18Rev. 2

NORM

Minimum '24 V DC

ARM

OFF, check emergency exit lightscome on

NORM

ON f check emergency exit lightscome on

ARM

BAT

EXT PWR (EPU caution light mustilluminate)

NORM

On

OFF, check cockpitdome light off

NORM

Off, or as required

ON, (check PRIMEPUMPS caution lighton, FU EL PRESSl.ights off)

OFF

ON (F PUMP XFERcaution light off)

OFF, (F PUMP XFERcaution light on)

LBA approved

(LB1210-A-15)

FLIGHT MBB - BK 117 B-1

EFFECTIVITY

4.3.3

SIN 7184 and subsequent

Interior check

Seat and pedals

Safety belts

Shoulder harness locks



- STATIC PRESS switch- GEN TRIP switch-- DG switch- FUEL VALVE I + 11

-- Adjust

-- Fasten, adjust

-- Function

-- OFF

- PRIMARY- NORM-- SLAVE- OP, guarded

I

Collective pitch (pilot/copilot)

All switches

Instrument panel

FIRE EXI switches

AGENT DISCH switch

FIRE DEl TEST switch

All switches and avionits

Clock

Overhead panel

All switches


Power levers

COLD START switch

HYD TEST switch

OAT



-- NORM

- OFF

- NORM


- Set

- OFF

- In

- OFF

- NORM

- NORM

- Check

LB244.11

Page 4 - 17Rev. 7

LBA approved

------------ MBB HELl COPTERS -----------FL IGHT MANUAL MBB -- BK 117 B-1

I EFFECTUVDTY

I

SiN 7184 and subsequent

Pre-start check

PWR SELECT switch - BAT

I

I

I

I

. Voltmeter indication

EMER LTS switch

PWR SELECT switch

PWR SELECT switch

EMER LTS switch

EMER LTS switch

PWR SELECT switch

- for battery start

- for EPU start

BUS-TIE switches (2)





- Minimum 24 V DC

- ARM

- OFF, check emergency exit lightscome on

- BAT

ON, check emergency exit lightscome on

- ARM

- Leave in BAT

- EXT PWR (EPU cau-tion light mustilluminate)

- ON

- ON, (check PRIMEPUMPS caution lighton, FUEL PRESSlights off)

- OFF

- ON (F PUMP XFERcaution light off)

- 0 FF, (F PUMP X FERcaution light on)

(LB 121O-A -30)

Page 4 - 18Rev. 2

LBA approved

eurocopteran EADS Company


- TEST

- Test - check lights come on

- CheckInstruments

Mast moment indicator

EFFECT/V/TV SIN 7176 and subsequent or after SB-MBB-BK117-90-101

Pre-start check (continued)


FUEL QTY indicator

MASTER warning light

ANN PNL TEST switch

CHIP DET TEST switch(spring- loaded)

CHIP DET TEST switch

AMM SEL switch

Trim actuator limit switches(only if DAFCS not installed)

Flight controls

Collective pitch

Rotor brake lever

Cyclic stick position

- Check quantity

- Reset

Push to test annunciator panel lights andcheck PITOT HEATER 1 and 2 cautionlights on the instrument panel, if installed

- Chip 1 (forewarded chip detectors) both ENG 1 CHIP and ENG 2 CHIP caution lights must come on.

- Chip 2 (aft chip detectors)both ENG 1 CHIP and ENG 2 CHIP caution lights must come on.

- GEN 11

- Check (check full travel of stick)

- Check free movement through full travel

Lock

- Check fully down (to check ROTORBRAKE caution light, pull the lever slightly and check fully down again)

- Centered I

EASA APPROVEDRev. 17 4 ... 19



4.4 STARTING ENGINES

4.4.1 Before starting engines

Fireguard (if available)

Rotor area

Anti-collision light

Posted

- Clear

- ON

4.4.2 Starting first engine

CAUTION IMMEDIATELY ABORT START AND, IF INDICATED, PERFORMMAINTENANCE ACTION BEFORE RESTART FOR ANY OF THEFOLLOWING:

• TOT RISES ABNORMALLY RAPIDLY ABOVE 800°C AND IS QUICKLY APPROACHING 899°C(If start is aborted but TOT limits are not exceeded, wait 15 secondsafter N1 RPM has returned to zero before attempting restart. This permits excess fuel to drain from combustion chamber.)

• NO POSITIVE ENGINE OR TRANSMISSION OIL PRESSUREINDICATIONS UPON REACHING GROUND IDLE CONDITION MAINTENANCE ACTIONI

• N2 RPM AND ROTOR RPM NEEDLES ARE NOT MATCHED AFTERREACHING STABILIZED GROUND IDLE CONDITIONMAINTENANCE ACTION!

• SUSPECTED BLADE STRIKE INTO VERTICAL STABILIZERS.Blade strike should be suspected if unusual noise or bang was audibleduring runup. Under gusty or turbulent wind conditions, especially withvertical wind components, and low rotor rpm (below 25%) main rotorblade(s) may strike the vertical stabilizer(s) - MAINTENANCE ACTIONI

ABORT START PROCEDURE

Power lever

Starter switch

- OFF

- ON for minimum 10 seconds as necessary to lower TOT (blowout)

4 - 20

NOTE • Either engine may be started first.

• If, for any reason a starting attempt is discontinued, the entire startingsequence must be repeated from the beginning.

EASA APPROVEDRev. 17



- Test - check lights come on

- Check

- TEST

Instruments

Mast moment indicator

EFFECTIVITY Up to SIN 7175, if SB-MBB-BK117-90-101 not incorporated

Pre...start check (continued)


FUEL QTY indicator

MASTER warning light

ANN PNL TEST switch

AMM SEL switch

Trim actuator limit switches(only if DAFCS not installed)

Flight controls

Collective pitch

Rotor brake lever

Cyclic stick

Check quantity

Reset

Push to test annunciator panel lights andcheck PITOT HEATER 1 and 2 cautionlights on the instrument panel, if installed

GEN 11

Check (check full travel of stick)

Check free movement through full travel

Lock

Check fully down (to check ROTORBRAKE caution light, pull the lever slightly and check fully down again)

Centered I

EASA APPROVEDRev. 17 4 -19

eurocopteran EADSCompany


4.4 STARTING ENGINES

4.4.1 Before starting engines

Fire guard (if available)

Rotor area

Anti-collision light

Posted

- Clear

- ON

4.4.2 Starting first engine

CAUTION IMMEDIATELY ABORT START AND, IF INDICATED, PERFORMMAINTENANCE ACTION BEFORE RESTART FOR ANY OF THEFOLLOWING:

• TOT RISES ABNORMALLY RAPIDLY ABOVE 800°C AND IS QUICKLY APPROACHING 899°C(If start is aborted but TOT limits are not exceeded, wait 15 secondsafter N1 RPM has returned to zero before attempting restart. This permits excess fuel to drain from combustion chamber.)

.. NO POSITIVE ENGINE OR TRANSMISSION OIL PRESSUREINDICATIONS UPON REACHING GROUND IDLE CONDITION MAINTENANCE ACTIONI

• N2 RPM AND ROTOR RPM NEEDLES ARE NOT MATCHED AFTERREACHING STABILIZED GROUND IDLE CONDITIONMAINTENANCE ACTIONI

• SUSPECTED. BLADE STRIKE INTO VERTICAL STABILIZERS.Blade strike should be suspected if unusual noise or bang was audibleduring runup. Under gusty or turbulent wind conditions, especially withvertical wind components, and low rotor rpm (below 25%) main rotorblade(s) may strike the vertical stabilizer(s) - MAINTENANCE ACTIONI

ABORT START PROCEDURE

Power lever

Starter switch

- OFF

- ON for minimum 10 seconds as necessary to lower TOT (blowout)

4 - 20

NOTE • Either engine may be started first

• If, for any reason a starting attempt is discontinued, the entire startingsequence must be repeated from the beginning.




Starting first engine (continued)

CAUTION. DO NOT EXCEED STARTER DUTY CYCLE.

• MONITOR CLOSELY TOT (STARTING TRANSIENT BETWEEN 836°CAND 899°C FOR MAXIMUM 12 SECONDS).

1. Respective fuel prime pump

2. Starter button

3. At 10 % N1

ON

Depress and hold. Simultaneously startclock.

Respective power lever move slowly toapprox. middle position between OFFand IDLE

NOTE • If light-off does not occur within 2 seconds, move power lever slowly forwarduntil light-off occurs. Power lever may be manipulated between middle positionand IDLE to stay within TOT limits.

• The ignition system is energized after passing the approx. 10° position ofpower lever travel range.

4. TOT

5. N2/NRO RPM increase

6. Engine and XMSN oil pressure

7. Respective power lever

8. At 40 % N1 (white dot)

9. At established IDLE RPM

10. Cyclic stick


Monitor, if necessary manipulate withpower lever

Monitor

- Check positive indication

Increase slowly to IDLE

- Starter button release

Respective generator ON, (check lightextinguished - on battery start only)

Centered

4 .. 21

I



EFFECTIVITY Up to SIN 7183

4.4.3 Starting second engine

11. Repeat items 1 to 9 of this procedure (on previous page)

12. After EPU starts

- PWR SELECT sw

- BUS-TIE switch

- GEN I + 1I lights

-EPU

- EPU light

13. FUEL PUMP XFER switches (2)

14. FUEL PUMP PRIME switches (2)

EFFECTIVITY After SB-BK117-90-117

14. PITOT HTR P and CP switches

EFFECTIVITY All

- BAT

- Check ON

- Check extinguished

- Disconnected


- ON

- OFF

- ONcheck PITOT HEATER 1 and 2 cautionlights off.

4 .. 22

NOTE ., FUEL PRESS warning lights may illuminate after switching off fuel primepumps.

It Operate engines at ground idle until engine minimum oil temperature (1 aOG)is reached.




Starting first engine (continued).

CAUTION. DO NOT EXCEED STARTER DUTY CYCLE.

• MONITOR CLOSELY TOT (STARTING TRANSIENT BETWEEN 836°CAND 899°C FOR MAXIMUM 12 SECONDS).

1. Respective fuel prime pump

2. Starter button

3. At 10 % Ni

ON

Depress and hold. Simultaneously startclock.

Respective power lever move slowly toapprox. middle position between OFFand IDLE

NOTE ., If light-off does not occur within 2 seconds, move power lever slowly forwarduntil light-off occurs. Power lever may be manipulated between middle positionand IDLE to stay within TOT limits.

• The ignition system is energized after passing the approx. 10° position ofpower lever travel range.

4. TOT

5. N2/NRO RPM increase

6. Engine and XMSN oil pressure

7. Respective power lever

8. At 40 % Ni (white dot)

9. At established IDLE RPM

10. Cyclic stick


Monitor, if necessary manipulate withpower lever

Monitor

Check positive indication

Increase slowly to IDLE

Starter button release

Respective generator ON, (check lightextinguished - on battery start only)

Centered

4 - 21

I



EFFECTIVITY SIN 7184 and subsequent

4.4.3 Starting second engine

11. Repeat items 1 to 9 of this procedure (on previous page)

12. After EPU starts

- PWR SELECT sw

- BUS-TIE switches (2)

- GEN 1+ I1 lights

-EPU

- EPU light

13. FUEL PUMP XFER switches (2)

14. FUEL PUMP PRIME switches (2)

EFFECTIVITY After SB-BK117-90-117

14. PITOT HTR P and CP switches

EFFECTIVITY All

- BAT

- Check ON


- Disconnected


- ON

- OFF

- ONcheck PITOT HEATER 1 and 2 cautionlights off.

4 .. 22

NOTE • FUEL PRESS warning lights may illuminate after switching off fuel prime

pumps.• Operate engines at ground idle until engine minimum oil temperature (1 aOG)

is reached.


FLIGHT MANUAL MBB -- BK 11

4.4.4 Cold weather start

Some general practices necessary for improved cold weather operat lon' are as follows:

1. When starting at low ambient temperature, oil pressure mayexceed 8.3 bar.

Pressure above 7.0 bar should not exist for more than approx.4.0 minutes.

2. If Nl acceleration to ground idle 1s slow or erratic when amb1enttemperature is lower than -26°C (-15 OF) and commerc1al Jet A orJet A-l fuel (JP-5) 1s used energ1ze the cold start sw1tch untilengine stabi11zes at ground 1dle.

It DO NOT LEAVE THE IICOLD START SWITCH"ENGAGED DURING OPERATION ABOVE 70 % N 1.

• ENSURE THAT THE COLD START SWITCH IS NOTINADVERTENTLY LEFT IN THE "COlO II POSITIONWHEN START ASSIST FUEL IS NOT REQUIRED.

• During coldstart at temperatures below -18 °C (0 OF)it may not be possible to achieve 10 % Nl RPM.At a minimum value of 7 % Nl, the power lever may beslowly advanced from the OFF position to achieveignition. Power lever may be manipulated as necessaryto accomplish the start within limits.

• It is generally recommended at temperatures below-30°C to preheat the battery to -30 °C or above.

• During engine start at low ambient temperature adelay of pointer movement may occur at the mastmoment indicator"and the triple tachometer.After warmup the indlcations are correct.

• After abrupt temperature changes from cold t~ warm(parking the helicopter in a heated hangar at lowambient temperatures) a complete loss of thelubricant at the main rotor pendulum absorbers mayoccur.

I

LB244.14

Page 4 - 23Rev. 7

LBA approved

FLIGHT MANUALMBB - BK1

4.5 System chec~s

4.5.1 * Hydraulic system check

I

NOTE

HARNING

CAUTION

• These checks may be performed between starting firstand second engine at pilot'.s discret1on.

• Before operating the HYD TEST switch 1n cold weatherconditions, some cyclic control inputs are necessaryto guarantee a perfect switch-over to system 2.

DO NOT TAKE OFF WITH A FAULTYHYDRAULIC SYSTEM.

• OBSERVE MAST MOMENT LIMITS DURINGCHECK.

• IF, AFTER CROSSOVER FROM SYSTEM 1TO SYSTEM 2 A RUNAWAY OF CYCLIC STICKOR COLLECTIVE PITCH OCCURS {INCREASEDCONTROL FORCES IN THE LONGITUDINAL-,LATERAL-, OR COLLECTIVE AXES), SWITCHOVER TO SYSTEM 1 IMMEDIATELY AND SHUTDOWN THE ENGINES.

Check the hydraulic systems (1 + 2) by small cyclic stick inputs inall four directions and slight up and down movements of thecollective pitch lever.

Power lever(s) of startedeng1ne(s)

Hydraulic pressureindications

Hydraulic system

HYD TEST switch

Hydraulic system 2

Hydraulic pressure indications

HYD TEST switch

- Check IDLE

- Check in the green

- Check

- Crossover to system 2(MASTER andHYD 1 ~ 2 lightsmust illuminate)

- Check

Check in the green

- Crossover to system 1(MASTER andHYD 1 ~ 2 lightsmust extinguish)

LBA approved

*

LB244.15


Page 4 -24Rev. 7

FLIGHT MBB-

4.5.2 * YAW CSAS system check (if installed - if 3-axis CSAS installed,refer to FMS 10-32)

INVERTER sw (one or both, as inst.) - ON

Perform CSAS system checks before each flight,after the hydraulic system checks are completed.

Circuit breakers CSAS YAW (2)and INV (1 or 2, as installed)

Artifictal horizon, pilot

YAN sequence switch

YAW sequence switch

YAW TEST switch

YAN TEST switch

STABILIZATION CUTOFFpushbutton (pilotls and cop1'ot ls s1de respectively)

YAW sequence sw1tch

- Check in; CSASYAWcaution and YAW OFFsegment lights are on

- Check warning flag (G)not showing

- Press; CSAS.YAW caut10nand YAW OFF segmentlights go off; YAW STBYsegment light comes on

- Press again; YAW STBYsegment light goes off

- TEST position; all YAWCSAS caution and segmentlights must come on

- Off, check detent lock;all YAW CSAS caution andsegment lights go off

- Press; all YAW CSAS cautionand segment lights come on

- Press twice to reengageYAW CSAS; all YAWCSAScaution and segment lightsgo off

II

*

NOTE .The helicopter should not be operated withthe YAW CSAS switched OFF, sinceSTANDBYand ON modes provide tail rotor drive shaftprotection against hard and abrupt pedal inputs.

To be checked before ea~h flight

LB104.110

Page 4 -25Rev. 5

LBA approved

4.5.3 * SPAS check

Cirrcuit breakers SPAS (2)and INV (1 or 2, as inst.)

INVERTER sw (1 or 2, as inst.)

SPAS toggle switch

FLIGHTMANUALMBB-BK

- Check in

- ON

- ON, then TEST andrelease

SPAS caution light - Check for illuminationafter approx. 4 seconds

If caution light fails to illuminate or if illumination occursimmediately after initiation of test procedure:

SPAS toggle switch

If test result positive:

SPAS toggle switch

4.5.4 * Avlon1c checks

COMM/NAV equipment

All other instruments andequipment

4.5.5* Miscellaneous checks

Optional equipment switches

- OFF/RESET; continue withSPAS switched OFF and notethat VNE is reduced by 15 kt

- OFF/RESET, then ONCheck caution lightSPAS extinguished

- On and check

- Check and set

- Set as required

4.5.6 Power check

Perform power check as required (see section 5).

4.5.7 Bleed air heating check

HTR SELECT switch

HTR switch

HTR switch

- BOTH

ON; check if ENG.l/ENG.2HEAT control lights comeon and TOT rises simultaneously

OFF; check if ENG.l/ENG.2HEAT control lights go offand TOT drops simultaneously

*

LB104.111


Page 4 - 26Rev. 6

LBA approved

EUROCOPTER FLIGHT MANUAL BK117 B-1

EFFECTIVITY If SFENA cyclic trim actuators installed (special configuration, if provisions forDAFCS installed).

4".5.8 *. Force Trim Release (FTR) function check

Power levers

FTR switch(pilot and copilot, respectively)

EFFECTIVITY All

- Check in IDLE position

- Press while making small cyclic inputs inall four directions; check that no springforces are present.

EFFECTIVITY SIN 7243·and "subsequent or after SB-MBB-BK117-90-103

4.5.9 Engine overspeed trip system check

CAUTION THE OVERSPEED TEST SWITCH SHALL ONLY BE OPERATED, WHENTHE POWER LEVER OF THE ENGINE TO BE CHECKED IS IN OR NEARTHE IDLE POSITION.

Power lever

of engine to be checked

of other engine

N2 speed of engine to be checked

IDLE

- Move smoothly to FLY position

- Check at 90 o

If N2 (engine to be checked) deviates from the 900/0 mark, adjust N2 ofrespective engine with power lever to achieve 900/0, in order to meet theoverspeed test trip speed.

OVERSPEED TEST switch

OVERSPEED TEST switch

- Select engine at IDLE (engine to bechecked); N2 speed must decrease

- OFF (middleposition); N2 speed must increase to previous value

Repeat procedure for second engine (first move power lever of idling engine smoothly upto FLY position, and then reduce the other to IDLE position).

NOTE If there is no significant engine response (N2-etrop) upon operation of theOVERSPEED TEST switch repeat the check with slightly higher/lower N2 (± 1%)settings.If there is still no significant engine response an overspeed trip systemmalfunction must be assumed.

EFFECTIVITY All


LBA APPROVEDRev. 9 4-26A

eurocopter FLIGHT MANUAL BK117 B-1an EADS Company

4.6 * PRE-TAKEOFF CHECK

1. Power levers Move smoothly to FLY position

2. Audio warning tone Check by reducing NR/N2 below 95%;ROTOR RPM warning and low rotorRPM audio tone must come on,then adjust NR/N2 back to 96%

3. Cyclic stick Check centering device secured I4. Engine and XMSN instruments In the green range

5. Fuel quantity Re-check

6. All caution and warning lights OFF

7. Bleed air consumers OFF

8. Optional equipment - As required

9. Collective pitch Unlock; check correct friction

4.7 * TAKEOFF CHECK

1. Hover flight Perform

2. N2/Rotor RPM - Adjust to 98 - 102%It is recommended to maintain 100%rotor RPM for steady flight condition

3. Torque Synchronize

4. Hover power Check

5. Engine and XMSN instruments Re-check


After takeoff:

7. Bleed air consumers - As required

4.8 PRE-LANDING CHECK

1. N2/Rotor RPM - Adjust to 98 - 102%

2. All instruments Check

3. All caution and warning lights Check



EASA APPROVEDRev. 17 4 - 27



EFFECT/V/TY Up to SIN 7183

4.9 ENGINE SHUTDOWN

NOTE • Check illumination of ROTOR RPM warning light plus continuous aural signalwhen the rotor RPM drop below 95%. If not fulfilled, entry in logbook andmaintenance action are required.

• Check illumination of ENG I LOW and ENG 11 LOW warning lights plusintermittent aural signal, when the N1 RPM of the engines drop below 60%. Ifnot fulfilled, entry in logbook and maintenance action are required.

• Set clock for a minimum ground idle run of 2 minutes to allow the engines tocool down.

I

I

1. Cyclic stick

2. Collective pitch

3. Power levers

4.

5. All consumers

6. Power levers

7. TOT and N1 drop

8. FUEL PUMP XFER (2)

9. Generators

10. Rotor brake

Check

Lock

IDLE, start clock

OFF except anti-collision light and transfer pumps

- After 2 minutes at IDLE, OFF

Monitor

OFF

OFF

- Apply below 50% RPM

NOTE In order to prevent oil coking it is recommended to motor the engines with starterfor 10 seconds (both power levers OFF). Start motoringappr. 30 seconds after N1needles have reached zero.

4 - 28

11. Anti-collision light

12. PWR SELECT switch

13. MASTER PWR switch

OFF

OFF

OFF


eurocopter FLIGHT MANUAL BK117 B-1an EADS Company

4.6 * PRE..TAKEOFF CHECK

1. Power levers Move smoothly to FLY position

2. Audio warning tone Check by reducing NR/N2 below 95%;ROTOR RPM warning and low rotorRPM audio tone must come on,then adjust NR/N2 back to 96%

3. Cyclic stick Check centering device secured

4. Engine and XMSN instruments In the green range

5. Fuel quantity Re-check



8. Optional equipment - As required

9. Collective pitch Unlock; check correct friction

4.7 * TAKEOFF CHECK

1. Hover flight Perform

2. N2/Rotor RPM - Adjust to 98 - 102%It is recommended to maintain 100%rotor RPM for steady flight condition

3. Torque Synchronize

4. Hover power Check

5. Engine and XMSN instruments Re-check


After takeoff:

7. Bleed air consumers - As required

4.8 PRE ..LANDING CHECK

1. N2/Rotor RPM - Adjust to 98 - 102%

2. All instruments Check

3. All caution and warning lights Check



EASA APPROVEDRev. 17 4 .. 27



EFFECTIVITY SIN 7184 and subsequent

4.9 ENGINE SHUTDOWN

NOTE • Check illumination of ROTOR RPM warning light plus continuous aural signalwhen the rotor RPM drop below 95%. If not fulfilled, entry in logbook andmaintenance action are required.

• Check illumination of ENG I LOW and ENG II LOW warning lights plusintermittent aural signal, when the Ni RPM of the engines drop below 60%. Ifnot fulfilled, entry in logbook and maintenance action are required.

• Set clock for a minimum ground idle run of 2 minutes to allow the engines tocool down.

I 1. Cyclic stick

2. Collective pitch

3. Power levers

4.

5. All consumers

6. Power levers

7. TOT and Ni drop

8. FUEL PUMP XFER (2)

9. Generators

10. Rotor brake

Check

Lock

IDLE, start clock

OFF except anti-collision light and transfer pumps

- After 2 minutes at IDLE, OFF

Monitor

OFF

OFF

- Apply below 50% RPM

NOTE In order to prevent oil coking it is recommended to motor the engines with starterfor 10 seconds (both power levers OFF). Start motoring appr. 30 seconds after Nineedles have reached zero.

4 .. 28

11. Anti-collision light

12. PWR SELECT switch

OFF

OFF


Documents

FLIGHT MANUAL BK117 B-1 - Regulations.gov...FLIGHT MANUAL BK117 B-1 0 - 11 EASA APPROVED Rev. 21 LIST OF EFFECTIVE PAGES NOTE N, R, or D indicate pages which are New, Revised or Deleted