2015- 07- 03

Saab Aircraft AB

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Matilda Krig

OFIC- 0- 2015- 0008

Saab AB, Aeronautics

S- 581 88 LINKÖPING Int + 46 13 18 20 00 Int + 46 13 18 44 95

Postal address

Saab Aircraft AB

Telephone Telefax

Nat 013 - 18 20 00

SWEDEN

Saab AB Nat 013 - 18 44 95

Page 1 (1)

To: All holders of an Airplane Flight Manual AFM 340 B, code 010.

Subject: Revision No. 28 Date: Mar 27/15

Page Code Reason for change

1- 4 010 Revised to reflect changes in this revision.

1- 5 010 - ”- .

1- 6 010 - ”- .

1- 7 010 - ”- .

2- 9 010 Eastman Turbo Oils (ETO) added as approved oils for engine and propeller gearbox.

The ETOs are identical to the corresponding BP Turbo Oils (e.g. ETO 2380 is identical to

BP Turbo Oil 2380).

2- 15 010 Mod. No. corrected. Previously 3313, now 3530.

2- 16 010 Limitation regarding flap setting for landing with TIMER master caution together with the

STAB light not illuminating (indicating a faulty STAB boot system) added.

4- 4 010 AOM Alert Operations Bulletin (AOB) No. 12 regarding “Ruptured de- ice boots”

implemented in AFM.

General information from AOB:

There has been reported events with ruptured de- ice boots on the horizontal tail. Recently

an event with a ruptured de- ice boot resulted in slight vibrations starting at a speed of

approximately 220 KIAS, with a gradual increase in vibrations with decreasing speed.

With flap 15 selected, a further increase in vibrations was noted. Selection of flap 20

resulted in a repetitive nose down pitch every 3 to 4 seconds together with rumbling and

shaking of the flight controls.

The nose down pitch was counteracted by pilot input and a go- around was initiated. The

aircraft made a flap- less (flap 0) landing with only slight vibrations felt in the flight controls.

The following recommendation from AOB added in Abnormal Procedure:

Should a TIMER master caution together with the STAB light not illuminating - indicating

a faulty STAB boot system - be experienced during flight, the landing shall be performed

as a flap 0 landing.

6- 2.11 010 A parenthesis added to clarify that the demonstrated crosswind values include gust.

REVISIONS TO SUPPLEMENTS

List of Supplements Date changed to reflect this revision.

Supplement Page Reason for change

No. 16, Operation on narrow runways All This supplement does not meet Australia’s current guidance

material in CAAP 235- 1(0) minimum Runway width and is

therefore cancelled.

REVISIONS TO APPENDICES

List of Appendices Date changed to reflect this revision.

With kind regards,

Saab AB

Matilda Krig
Airplane Flight Manual

RECORD OF REVISIONS - AFM 340B 010

Rev.

No.

Date By Rev.

No.

By Rev.

No.

By

1

2

3

4

5

6

7

8

9

10

11

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13

14

15

Jan 12/96

Jan 30/96

Mar 22/96

Jun 26/96

Oct 16/96

Nov 12/96

Jun 02/97

Dec 05/97

Mar 31/98

Mar 12/99

Oct 01/99

Nov 03/00

Jun 01/01

Dec 03/01

Jan 31/03

Date Date

16 Dec 05/03

17 Nov 10/04

18 Feb 25/05

19 Jan 05/07

20 Oct 05/07

21 Nov 30/07

22 Aug 20/08

23 Feb 26/10

24 Feb 17/11

25 Aug 31/12

26 Nov 22/13

27 Aug 14/14

28 Mar 27/15
GENERAL

Airplane Flight Manual

WT

AFM 340B Code 010 Page 1- 4

LIST OF EFFECTIVE PAGES

The following pages comprise the Airplane Flight Manual for SAAB 340B airplanes with Mod. No. 2571

- Extended Wing Tips - installed, whose registration authority accepts/approves the use of the

EASA/FAA standard version manual for flight operations.

REVISION No. 28 DATE: Mar 27/15

APPROVED BY EASA under approval No. 10053909 on 2nd Jul 2015.

ACCEPTED by FAA in letter No. ANM- 116- 15- 335.

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

TITLE

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INTRO 0

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SECTION 1

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Mar 27/15

Feb 17/11

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SECTION 3

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SECTION 6

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2.3

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Feb 25/05

Nov 30/95

R=REVISED (to be replaced) D=DELETED (to be removed) N=NEW (to be introduced)

(TR = Temporary Revision)

EASA Approved Mar 27/15
GENERAL

Airplane Flight Manual

WT

AFM 340B Page 1- 5 Code 010

LIST OF EFFECTIVE PAGES (Cont’d)

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

SECTION 6

2.17

2.18

2.19

2.20

2.21

2.22

2.23

2.24

2.25

2.26

2.27

2.28

2.29

2.30

2.31

2.32

2.33

2.34

2.34

2.35

2.35

2.36

2.36

2.37

2.37

2.38

2.38

2.39

2.39

2.40

2.40

2.41

2.42

2.43

3

3.1

3.2

3.3

3.4

3.5

(CONT)

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Feb 17/11

Nov 30/95

SECTION 6

3.6

3.7

3.8

3.9

3.10

3.11

3.12

3.13

3.14

3.15

3.16

3.17

3.18

3.19

3.20

3.21

3.22

3.23

3.24

3.25

3.26

3.27

3.28

3.29

3.30

3.31

3.32

3.33

3.34

4

4.1

4.2

4.3

4.4

4.5

4.6

4.7

4.8

4.9

4.10

(CONT)

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SECTION 6

4.11

4.12

4.12A

4.13

4.13A

4.14

4.14A

4.15

4.16

4.17

4.18

4.19

4.20

4.21

4.21A

4.22

4.23

4.23

4.24

4.25

4.25

4.26

4.27

5

5.1

5.2

5.3

5.4

5.5

5.6

5.7

5.8

5.9

5.10

5.11

5.12

5.12A

5.13

5.13A

5.14

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EASA Approved Mar 27/15
GENERAL

Airplane Flight Manual

WT

AFM 340B Page 1- 6 Code 010

LIST OF EFFECTIVE PAGES (Cont’d)

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

SECTION 6

5.14A

5.15

5.16

5.17

5.18

5.19

5.20

5.21

5.21A

6

6.1

6.2

6.3

6.4

6.5

6.6

6.7

6.8

6.9

6.10

6.11

6.12

6.12A

6.13

6.13A

6.14

6.14A

6.15

6.16

6.17

6.18

6.19

6.20

6.21

6.21A

7

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7.2

(CONT)

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SECTION 6

7.3

7.4

7.5

7.6

7.7

7.8

7.9

7.10

7.11

7.12

7.12A

7.13

7.13A

7.14

7.14A

7.15

7.16

7.17

7.18

7.19

7.20

7.21

7.21A

8

8.1

8.2

8.3

8.4

8.4A

8.5

8.5

8.6

8.6

8.7

8.7

8.8

8.8

(CONT)

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Jun 01/01

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Feb 17/11

Dec 03/01

Jun 01/01

Dec 03/01

Jun 01/01

SECTION 6

9

9.1

9.2

9.3

10

10.1

10.2

10.2

10.3

10.3

10.4

10.4

10.5

10.5

10.6

10.6

10.7

10.7

10.8

10.8

10.9

10.9

10.10

10.11

11

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11.2

11.2

11.3

11.3

11.4

11.4

11.5

11.5

11.6

11.6

11.7

11.7

(CONT)

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Nov 03/00

Jun 01/01

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Feb 17/11

Nov 03/00

Jun 01/01

Nov 03/00

Jun 01/01

Nov 03/00

Jun 01/01

EASA Approved Mar 27/15
GENERAL

Airplane Flight Manual

WT

AFM 340B Page 1- 7 Code 010

LIST OF EFFECTIVE PAGES (Cont’d)

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

SECTION 6

11.8

11.8

11.9

11.9

11.10

11.11

12

12.1

12.2

12.3

12.4

12.5

12.6

12.7

12.8

12.8A

12.9

12.9A

12.10

12.10A

12.11

12.12

12.13

12.14

12.15

12.16

12.17

12.17A

12.18

12.18A

(CONT)

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SECTION 6

12.19

12.19A

12.20

12.21

12.22

12.23

12.24

12.25

12.26

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12.27

12.27A

12.28

12.28A

12.29

12.30

12.31

12.32

12.33

12.34

12.35

12.35A

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12.37

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SECTION 6

13

13.1

13.2

13.3

13.4

13.5

13.6

13.7

SECTION 7

SUPPLEMENTS

SECTION 8

APPENDICES

(CONT)

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Mar 31/98

Dec 05/97

Dec 05/03

Feb 26/10

Dec 05/97

Feb 25/05

Feb 25/05

Dec 05/03

EASA Approved Mar 27/15
LIMITATIONS Airplane Flight Manual

WT

AFM 340B Page 2- 9 Code 010

OIL SYSTEM

Approved types of oil (engine and propeller gearbox)

Type I oils: Type II oils:

BP Turbo Oil 2389 Aero Shell Turbine Oil 500

ETO 2389 Castrol 205

Exxon Turbo Oil 2389 BP Turbo Oil 2380

Castrol 325 ETO 2380

Exxon Turbo Oil 2380

Mobil Jet II

Stauffer Jet II

Approved types of oil (engine only)

Type I oils: Type II oils:

Mobil Jet 254

NOTE

It is not allowed to mix Mobil Jet 254 oil with other approved oils.

NOTE

1. Minimum oil temperature for engine start with type II oil is - 40 oC (- 40 oF).

2. Mixing of type I and II oils is allowed but not recommended.

FUEL SYSTEM

The total quantity of usable fuel is 5690 lbs (2580 kg) at a fuel density of 6.7 lbs/US gal. (0.802 kg/L).

Fuel remaining in the tanks when the fuel quantity indicators read zero in level flight cannot be safely used in all

flight conditions.

Fuel anti- ice additives meeting specification Mil 27686E or Mil 85470B are authorized for use.

Concentration shall be 0.06 % min to 0.15 % max by volume.

cont’d...

EASA Approved Mar 27/15
These speeds already include an increment

for maneuvering up to 30 degrees of bank.

LIMITATIONS Airplane Flight Manual

WT

AFM 340B Page 2- 15 Code 010

AIRSPEEDS (Cont’d)

MINIMUM AIRSPEEDS FOR ICING CONDITIONS

The minimum airspeeds below must be used for operation in icing conditions and, with Mod. No. 3530 installed

(improved stall warning system) whenever the blue ICE SPD status light is illuminated.

Definitions

VCLEAN = Final climb speed in accordance with Final Climb charts in section 6- 4.

Maneuvering = A bank angle in excess of 15 degrees in a coordinated turn.

General

10 knots shall be added to the speeds below for maneuvering with bank angles between 15 and 30 degrees.

At higher bank angles, increase speed by 10 knots for each 10 degrees of bank above 30.

For all- engines operating climb below minimum sector altitude (MSA):

Maintain a minimum speed of “Enroute Climb Speed - with residual airframe and propeller ice” (VCLEAN +13)

after transitioning to the Enroute Climb configuration (after initial power reduction from Take- off power).

For all- engines operating climb above minimum sector altitude (MSA), cruise, descent, holding

and approach:

Flaps 0 160 KIAS ............

Flaps 7 150 KIAS ............

Flaps 15 145 KIAS ............

Flaps 20 140 KIAS ............

Flaps 35 130 KIAS ............

If a lower airspeed must be used to exit the icing conditions, “Enroute Climb Speed - with residual airframe and

propeller ice” (VCLEAN +13) may also be used for flaps 0 climb.

For single- engine climb after transitioning to the Enroute Climb configuration (after initial power

reduction from Take- off power) and for driftdown:

Flaps 0 “Enroute Climb Speed - with residual airframe and propeller ice” (V ............ CLEAN +13).

For final approach:

VREF +10

Increase landing distance for the 10- knot speed increment applied to the reference speed in accordance with

the performance data in Section 6 of this manual.

For missed approach/go- around:

Maintain a minimum speed of “Approach Climb Speed - with residual airframe and propeller ice” until above

minimum sector altitude (MSA), then the speeds specified above.

EASA Approved Mar 27/15
LIMITATIONS Airplane Flight Manual

WT

AFM 340B Page 2 Code 010 −16

SYSTEMS

Cabin Pressurization

Maximum Differential Pressure 7.5 psi (52.0 kPa) ..............

Auto Mode Schedule 7.1 psi (50.0 kPa) .......................

Flight Director

Use of flight director information in go−around mode during take−off is not authorised.

Autopilot

− In icing conditions, as defined in the “ICING CONDITIONS” section for adherence to autopilot/flight director

limitations, if the flight director and/or autopilot are engaged in a vertical mode during climb, IAS mode must

be used.

− Following an engine failure it is required to disconnect the autopilot and re−trim the 

aircraft before re−engagement of the autopilot.

− Minimum Use Heights (MUH):

 During take−off or go−around: 200 ft AGL (Above Ground Level)

 For aircraft operating under LFV approval, the following additional limitations apply:

 (Not required for operation according to FAA regulations)

− Minimum Use Heights (MUH):

 During cruise: 500 ft AGL

 During coupled approach: 50 ft AGL

 During non−coupled approach: 100 ft AGL.

Yaw Damper

Yaw Damper Operation is not authorised for:

− Take−off

− Go around

− Landing.

Flaps

− Flaps may only be extended on ground and during take off, low altitude holding, approach and landing, up to

a maximum altitude of 14000 ft.

− Landing Flap to be selected before 300 ft radio height during normal landing.

During flight with Master Caution (ICE PROT) and Timer light illuminated and green STAB light not

illuminating, Flaps 0 must be used for landing (required by AD). For landing procedure see Section 4 Abnormal

Procedures, Ice Protection Fault.

cont’d...

EASA Approved Mar 27/15
ABNORMAL

PROCEDURES Airplane Flight Manual

WT

AFM 340B Code 010 Page 4−4

RUDDER LIMITER LIGHT ON

Reduce speed until light goes out but not below 140 kts. If light still is ON at 140 kts, select the rudder limiter

switch to OVERRIDE. Max speed with the rudder limiter in OVERRIDE is 180 KIAS. Avoid large rudder deflections above 150 KIAS. If rudder limiter light is on below 140 KIAS, use if possible a runway with less than 10 kts

crosswind for landing.

HYDRAULIC WARNING

Switch off the hydraulic pump.

− If both emergency and main pressures are low, extend the landing gear and land at the nearest suitable

airport. Leave flaps in present position; use hand pump if brake pressure needs to be restored.

− If only emergency pressure low, use hand pump for landing gear, flap and brake operation.

− If only main pressure is low, set the hydraulic pump to OVERRIDE; if main pressure increases, switch

between OVERRIDE and OFF so as to maintain pressure. If there is no increase in pressure during

override, set the pump to OFF and use the hand pump for landing gear, flap and brake operation.

− If main pressure and hydraulic quantity are low, pull emergency landing gear handle for gear extension.

Leave flaps in present position and use hand pump if brake pressure needs to be restored.

− If all pressures are normal, use hand pump for landing gear, flap and brake operation.

AC GENERATOR FAULT

Try to reset the generator once. If it will not reset, set the generator switch to OFF/R and leave icing conditions

if possible.

ICE PROTECTION SYSTEM FAULT

Reset affected switch once. If the airframe or powerplant de−icing/anti−icing system is not restored, leave

icing conditions if possible.

During landing with iced−up or inflated de−ice boots, use the following flap settings and speeds:

Wing fault: Flaps 20 and VREF20+10 KIAS or Flaps 35 and VREF35 + 10 KIAS

Stabilizer fault, or

Wing and

stabilizer fault: Flaps 20 and VREF20 + 10 KIAS 

During landing with Master Caution (ICE PROT) and TIMER light illuminated and green STAB light not

illuminating, use the following flap settings and speeds (required by AD) :

Flaps 0 and VREF20 + 30 KIAS

ALTERNATE EXTENSION OF LANDING GEAR

Select landing gear down and use the hand pump to extend the landing gear. Hand pump selector must be set

to LDG GR position.

If an emergency extension has to be made, pull the emergency landing gear handle, then set landing gear

handle to DOWN.

EASA Approved Mar 27/15
PERFORMANCE

DEFINITIONS AND

Airplane Flight Manual

WT

GENERAL DATA

AFM 340B Page 6- 2.11 Code 010

WIND COMPONENTS

Wind Components

The conversion of reported wind velocities to headwind, tailwind and crosswind components is illustrated by

the wind components chart on the following page.

Maximum Demonstrated Crosswind Component

Maximum Demonstrated Crosswind Component is 35 knots (including gust).

This was demonstrated on a dry runway and was not found to be limiting.

Example

Entering the chart with a reported wind velocity which has a speed of 35 knots at a direction of 40  relative to

the runway:

the crosswind component is 22.5 knots

the headwind component is 26.8 knots.

EASA Approved Mar 27/15
SUPPLEMENTS

Airplane Flight Manual

WT

EASA Approved Mar 27/15 AFM 340B Code 010 Section 7

LIST OF SUPPLEMENTS APPLICABLE TO AFM 340B 010

The following Supplements may/must be used as a complement to this AFM:

Approved by EASA under approval No. 10053909 on 2nd Jul 2015. DATE: Mar 27/15

Accepted by FAA in letter No. ANM- 116- 15- 335.

No. Supplements Latest

Revision

Approval

date

2 Omega/VLF Operation with Ferry Flight Kit 2 Oct 16/96

4 CAT II Operation 3 Oct 16/96

12 Operation on unpaved runways (Australian CAA standard) 3 Aug 31/12

13 Traffic alert and Collision Avoidance System (TCAS II) 8 Dec 15/14

16 Operation on narrow runways (Australian CAA standard) 1 Deleted

17 Freon Air Conditioning 1 Oct 16/96

18 Ferry GPS Kit 1 Oct 16/96

19 HF Com Ferry Flight Kit 1 Oct 16/96

24 ITT Exceedance during take- off or go- around 2 Oct 16/96

39 Search and Rescue - 200 (SAR- 200)* 7 Nov 15/13

43 Operation with increased T/O speeds and high airfield

performance

4 Feb 17/11

46 Operation with Autocoarsen inoperative 1 Oct 01/99

48 Extended operation with JP- 4 fuel* 1 Feb 27/98

49 Precipitation Covered and Low Friction Runway Operation

(JAA standard)*

First Issue Dec 05/97

53 Airborne Collision Avoidance System (ACAS II) 1 Dec 03/01

54 Landing with tailwind above 10 knots* 1 Nov 13/09

57 GPS Based FMS Non Precision Approach 1 May 05/04

59 P- RNAV Operation* 4 Aug 14/14

62 ADS- B Surveillance (ADS- B- NRA) First Issue Feb 20/12

* Distribution limited to particular operators.
APPENDICES

Airplane Flight Manual

WT

AFM 340B Code 010 Section 8

LIST OF APPENDICES APPLICABLE TO AFM 340B 010

The following Appendices may be used as a complement to this AFM:

Approved by EASA under approval No. 10053909 on 2nd Jul 2015. DATE: Mar 27/15

Accepted by FAA in letter No. ANM- 116- 15- 335.

Appendices Latest

Revision

Approval

date

Configuration Deviation List 12 Nov 22/13

Operation with Derated Power on the CT7- 9B, Simplified method (WT) 3 Dec 03/01

Operation with Reduced Take- off Power (WT) 6 Dec 05/03

EASA Approved Mar 27/15