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 3 APR 02, 1990
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 10 APR 29, 2003
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)
FLIGHT MANUAL BK117 B-1
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 Remove and dis-pose of superseded pages, insert the latest revision pages and complete the Record of Revi-sions as necessary.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 0-12 21 List of effective pages
R 0-13 21 List of effective pages
R 0-14 21 List of effective pages
R 0-15 21 List of effective pages
R 0-16 21 List of effective pages
R 0-17 21 List of effective pages
R 0-18 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
Page RevNo. Remarks/Effectivity
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
FLIGHT MANUAL BK117 B-1
0 - 12EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
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
Page RevNo. Remarks/Effectivity
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
FLIGHT MANUAL BK117 B-1
0 - 13EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
3-39 14
3-40 14
3-41 14
3-42 14
3-43 14
3-44 14
3-45 14
3-46 14
3-47 14
3-48 14
3-49 14
3-50 14
3-51 14
3-52 14
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
Page RevNo. Remarks/Effectivity
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
FLIGHT MANUAL BK117 B-1
0 - 14EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
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
5-26 8
5-27 8
5-28 8
5-29 8
5-30 8
5-31 8
5-32 8
5-33 8
5-34 8
5-35 8
5-36 8
5-37 8
5-38 8
5-39 8
5-40 8
5-41 8
5-42 8
5-43 8
5-44 8
Page RevNo. Remarks/Effectivity
5-45 8
5-46 8
5-47 8
5-48 8
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
FLIGHT MANUAL BK117 B-1
0 - 15EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
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
10-2 15 Log of Supplements
10-3 15 Log of Supplements
10-4 15 Log of Supplements
10-5 15 Log of Supplements
10-6 15 Log of Supplements
10-7 15 Log of Supplements
10-8 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
Page RevNo. Remarks/Effectivity
10-2-6 20
10-2-7 20
10-2-8 20
10-2-9 20
10-2-10 20
10-2-11 20
10-2-12 20
10-2-13 20
10-2-14 20
10-2-15 20
10-2-16 20
10-3-1 0
10-3-2 0
10-3-3 0
10-3-4 0
10-3-5 0
10-3-6 0
10-3-7 0
10-3-8 0
10-3-9 0
10-3-10 0
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
10-6-2 4
10-6-3 4
10-6-4 4
10-7-1 0
10-7-2 0
FLIGHT MANUAL BK117 B-1
0 - 16EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
10-7-3 0
10-7-4 0
10-7-5 0
10-8-1 0
10-8-2 8
10-8-3 0
10-8-4 0
10-8-5 0
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
10-15-5 5
10-15-6 5
10-16-1 0
10-16-2 0
10-16-3 0
10-17-1 0
10-17-2 0
Page RevNo. Remarks/Effectivity
10-17-3 0
10-17-4 0
10-17-5 0
10-18-1 0
10-18-2 5
10-18-3 0
10-18-4 0
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
10-28-1 0
10-28-2 0
10-29-1 0
10-29-2 0
10-29–3 0
10-29-4 0
10-30-1 3
FLIGHT MANUAL BK117 B-1
0 - 17EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
10-30-2 3
10-30-3 3
10-31-1 0
10-31-2 0
10-31-3 0
10-31-4 0
10-31-5 0
10-31-6 0
10-31-7 0
10-31-8 0
10-32-1 18
10-32-2 18
10-32-3 18
10-32-4 18
10-32-5 18
10-32-6 18
10-32-7 18
10-32-8 18
10-32-9 18
10-32-10 18
10-32-11 18
10-32-12 18
10-32-13 18
10-33-1 0
10-33-2 0
10-33-3 0
10-33-4 0
10-33-5 0
10-34-1 0
10-34-2 5
10-34-3 7
10-34-4 3
10-35-1 20.1
10-35-2 20.1
10-35-3 20.1
10-35-4 20.1
10-35-5 20.1
10-35-6 20.1
10-35-7 20.1
Page RevNo. Remarks/Effectivity
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
10-35-14 20.1
10-35-15 20.1
10-35-16 20.1
10-35-17 20.1
10-35-18 20.1
10-35-19 20.1
10-35-20 20.1
10-35-21 20.1
10-37-1 0
10-37-2 0
10-37-3 0
10-37-4 0
10-38-1 0
10-38-2 0
10-38-3 0
10-38-4 0
10-38-5 0
10-38-6 0
10-38-7 0
10-38-8 0
10-38-9 0
10-38-10 0
10-38-11 0
10-38-12 0
10-38-13 0
10-38-14 0
10-38-15 0
10-39-1 0
10-39-2 0
10-39-3 0
10-39-4 0
10-39-5 0
10-39-6 0
FLIGHT MANUAL BK117 B-1
0 - 18EASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
10-39-7 0
10-39-8 0
10-39-9 0
10-40-1 0
10-40-2 0
10-40-3 0
10-40-4 5
10-40-5 5
10-40-6 0
10-40-7 0
10-40-8 0
10-40-9 0
10-40-10 0
10-41-1 0
10-41-2 2
10-41-3 0
10-41-4 5
10-41-5 0
10-41-6 0
10-41-7 2
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
Page RevNo. Remarks/Effectivity
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
10-47-5 0
10-47-6 5
10-47-7 0
10-47-8 0
10-47-9 0
10-48-1 3
10-48-2 4
10-48-3 3
10-48-4 7
10-48-5 7
10-48-6 3
10-48-7 3
10-48-8 3
10-48-9 3
10-48-10 3
10-48-11 5
10-48-12 3
10-48-13 3
10-48-14 3
10-48-15 3
10-48-16 3
10-48-17 4
10-48-18 4
10-48-19 4
10-48-20 4
10-48-21 4
10-48-22 4
10-48-23 4
10-48-24 4
10-48-25 5
FLIGHT MANUAL BK117 B-1
0 - 18AEASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
10-48-26 3
10-48-27 3
10-48-28 3
10-48-29 3
10-48-30 3
10-48-31 3
10-48-32 3
10-48-33 3
10-48-34 3
10-48-35 3
10-48-36 3
10-48-37 3
10-48-38 3
10-48-39 3
10-48-40 3
10-48-41 3
10-48-42 3
10-48-43 3
10-48-44 3
10-48-45 3
10-48-46 3
10-48-47 3
10-48-48 3
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
Page RevNo. Remarks/Effectivity
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
FLIGHT MANUAL BK117 B-1
0 - 18BEASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
10-66-6 9
10-66-7 7
10-66-8 7
10-66-9 7
10-66-10 7
10-66-11 7
10-66-12 7
10-66-13 7
10-66-14 7
10-66-15 7
10-66-16 7
10-66-17 7
10-66-18 7
10-66-19 7
10-66-20 7
10-66-21 7
10-66-22 7
10-66-23 7
10-66-24 7
10-66-25 7
10-66-26 7
10-66-27 7
10-67-1 7
10-67-2 7
10-67-3 7
10-67-4 7
10-67-5 7
10-67-6 7
10-67-7 7
10-67-8 7
10-68-1 9
10-68-2 9
10-68-3 9
10-68-4 9
10-68-5 9
10-68-6 9
10-69-1 9
10-69-2 9
10-69-3 9
Page RevNo. Remarks/Effectivity
10-69-4 9
10-69-5 9
10-69-6 9
10-69-7 9
10-69-8 9
10-69-9 9
10-69-10 9
10-69-11 9
10-69-12 9
10-69-13/-14 9
10-71-1 9
10-71-2 9
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
11-1-15 3
11-1-16 3
11-1-17 3
11-1-18 3
11-1-19 3
FLIGHT MANUAL BK117 B-1
0 - 18CEASA APPROVED
Rev. 21
Page RevNo. Remarks/Effectivity
11-1-20 3
11-1-21/-22 3
11-1-23 3
11-1-24 3
11-1-25 3
11-1-26 3
11-1-27 3
11-1-28 8
11-1-29 3
11-1-30 3
11-1-31 8
11-1-32 8
11-1-33 3
11-1-34 8
11-1-35 8
11-1-36 8
11-1-37 8
11-1-38 8
11-1-39/-40 8
11-1-41 8
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
Page RevNo. Remarks/Effectivity
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
Center control panel
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
Center control panel
II
*
All switches and avionicsexcept:
FUEL VALVE I + I1
Collective pitch
All switches
Overhead panel
All circuit breakers
All switches
Power levers
Instrument panel
FIR E EXT switches
AGENT DISCH switch
Ft RE DET TEST switch
All switches and avionics
Center control panel
PWR SELECT switch
Voltmeter indication
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)
FLIGHT MANUAL BK117 B–1
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
FLIGHT MANUAL BK117 B–1
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
FLIGHT MANUAL BK117 B–1
EASA APPROVEDRev. 20.1 4 - 9
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
FLIGHT MANUAL BK117 B–1
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
---------- 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
* To be checked before each flight
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
* To be checked before each flight
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
Fuselage - right side
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
* To be checked before each flight
Page 4 ;... 14Rev. 0
LBA approved
(LB1210-A-11)
FLIGHT MANUAL BK117 B–1
EASA APPROVEDRev. 20.1 4 - 15
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
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
Cockpit door - Condition, function
Cyclic stick - Secured, safety-wired
Copilot seat and safety belts - Condition
L For single pilot flights:Copilot’s safety belts
- Fastened, secured
L Static ports (2) - Clear
L To be checked before each flight
FLIGHT MANUAL BK117 B–1
EASA APPROVEDRev. 20.14 - 16
Fuselage - left side (continued)
Drain port - Clear
L Pitot tube - Clear, condition
L Pedal area - No foreign objects
Lower cockpit window - Condition
Cockpit air intake - 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
L To be checked before each flight
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
Center control panel
All switches and avionicsexcept:
- 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
All switches and avionics
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
- OFF orneutral position
- 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
Voltmeter indication
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
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
Center control panel
All switches and avionicsexcept:
- 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
All circuit breakers
Power levers
COLD START switch
HYD TEST switch
OAT
To be checked before each flight
- OFF orneutral position
-- NORM
- OFF
- NORM
- OFF orneutral position
- 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)
FUEL PUMP PRIME switches
FUEL PUMP PRIME switches
FUEL PUMP XFER switches
FUEL PUMP XFER switches
- 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
FLIGHT MANUAL BK117 B-1
- 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)
FIRE DET TEST switch
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
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
- 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)
FIRE DET TEST switch
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
FLIGHT MANUAL BK117 B-1
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.
EASA APPROVEDRev. 17
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
EASA APPROVEDRev. 17
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
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
- Check extinguished
- 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.
EASA APPROVEDRev. 17
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
EASA APPROVEDRev. 17
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
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
- Check extinguished
- Disconnected
- Check extinguished
- 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.
EASA APPROVEDRev. 17
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
To be checked before each flight
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
To be checked before each flight
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
* To be checked before each flight
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
6. All caution and warning lights OFF
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
4. Bleed air consumers OFF
* To be checked before each flight
EASA APPROVEDRev. 17 4 - 27
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
EASA APPROVEDRev. 17
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
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
6. All caution and warning lights OFF
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
4. Bleed air consumers OFF
* To be checked before each flight
EASA APPROVEDRev. 17 4 .. 27
eurocopteran EADS Company
FLIGHT MANUAL BK117 B-1
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
EASA APPROVEDRev. 17