2015- 07- 03 Saab Aircraft AB Handled by

Date

Your date Reference

Your reference Matilda Krig
OFIC- 0- 2015- 0006 Saab AB, Saab Aerosystems

Int + 46 13 18 20 00 Int + 46 13 18 44 95 S- 581 88 LINKÖPING Postal address Saab Aircraft AB Telephone Telefax Nat 013 - 18 20 00

SWEDEN Nat 013 - 18 44 95 Saab AB Page 1 (1) To: All holders of an Airplane Flight Manual AFM 340 B, code 001.
Subject: Revision No. 35 Date: Mar 27/15
Page Code Reason for change 1- 4 001 Revised to reflect changes in this revision. 1- 5 001 - ”- . 1- 6 001 - ”- . 2- 9 000 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- 15 000 Mod. No. corrected. Previously 3312, now 3529. 2- 16 001 Limitation regarding flap setting for landing with TIMER master caution together with the STAB light not illuminating (indicating a faulty ST AB boot system) added. 2- 17 000 Page shift. 4- 4 000 Deleted. 4- 4 001 New page, unique to the code 001 AFM. 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- 2.11 000 A parenthesis added to clarify that the demonstrated crosswind values include gust.

REVISIONS TO SUPPLEMENTS List of Supplements Date changed to reflect this revision.

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 001

Rev. No. Date By Rev. No. By Rev. No. By

1

2

3

4

5

6

7

8

9

10

11

12

13

14

15 Aug 15/89
Nov 14/89
Jan 17/90
Apr 23/90
Sep 07/90
Jun 20/91
Apr 01/92
Jun 23/92
Aug 07/92
Mar 15/95
Nov 23/95

Jan 30/96
Oct 16/96
Nov 01/96
Nov 12/96 Date Date

16 Jun 02/97

17 Mar 12/99

18 Oct 01/99

19 Nov 03/00

20

21

22

23

24

25

26

27

28

29

30 Feb 09/01
Sep 07/01
Mar 15/02
Dec 06/02

Dec 05/03
Nov 10/04
Feb 25/05

Jan 30/06
Oct 05/07
Nov 30/07
Aug 20/08 31

32

33

35 Feb 26/10

Feb 17/11 Aug 31/12

Mar 27/15 34 Aug 14/14

### Airplane Flight Manual GENERAL

AFM 340B Page 1- 4 Code 001 

### LIST OF EFFECTIVE PAGES The following pages comprise the Airplane Flight Manual for SAAB 340B airpl anes, whose registration authority accepts/approves the use of the U.S. Federal Aviation Administration standard version manual for flight operations. 

### REVISION No. 35 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
1

INTRO 0 1 2 3

SECTION 1
1 2 3 R 4 R 5 R 6 7

SECTION 2
1 2 3 4 5 6 7 8 R 9 10 001

000 000 000

000 000 000 001 001 001 001

000 001 000 000 000 000 000 000 000 001 Aug 15/89

Oct 16/96 Feb 26/10 Mar 15/95

Feb 09/01 Feb 26/10 Oct 16/96 Mar 27/15 Mar 27/15 Mar 27/15 Aug 14/14

Feb 26/10 Feb 26/10 Feb 26/10 Feb 26/10 Feb 26/10 Aug 31/12 Feb 26/10 Feb 26/10 Mar 27/15 Feb 17/11 SECTION 2
11 12 13 14 R 15 R 16 R 17 18 19 20

SECTION 3
1 2 3 4 5 6 7 8

SECTION 4
1 2 3 D 4 N 4 5 6 (CONT)
001 000 000 000 000 001 000 000 000 001

001 000 000 000 000 000 000 001

000 000 000 000 001 000 000 Feb 17/11 Aug 14/14 Feb 26/10 Feb 26/10 Mar 27/15 Mar 27/15 Mar 27/15 Feb 26/10 Feb 26/10 Feb 26/10

Nov 23/95 Mar 15/95 Dec 05/03 Feb 26/10 Mar 15/95 Mar 15/95 Dec 03/01 Nov 23/95

Aug 31/12 Mar 15/95 Mar 15/95 Nov 03/00 Mar 27/15 Aug 31/12 Mar 15/95 SECTION 5
1 2 3 4 5 6 7 8

SECTION 6
0
1 2 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 2.10 001 000 000 000 000 000 000 001

000
000 000 000 001 000 000 000 000 000 000 000 000 Feb 26/10 Mar 15/95 Aug 14/14 Feb 17/11 Aug 14/14 Feb 26/10 Feb 26/10 Feb 26/10

Feb 09/01
Mar 15/95 Mar 15/95 Nov 23/95 Mar 15/95 Feb 26/10 Mar 15/95 Mar 15/95 Mar 15/95 Oct 16/96 Feb 17/11 Feb 17/11 Nov 30/07

EASA Approved Mar 27/15

### Airplane Flight Manual GENERAL

AFM 340B Page 1- 5 Code 001 

### LIST OF EFFECTIVE PAGES (Cont’d)

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

SECTION 6
R 2.11 2.12 2.13 2.14 2.15 2.16 2.17 2.18 2.19 2.20 2.21 2.22 2.23 2.24 2.25 2.26 2.26 2.27 2.27 2.28 2.28 2.29 2.29 2.30 2.30 2.31 2.31 2.32 2.32 2.33 2.34
3 3.1 3.2 3.3 3.3A 3.3B 3.4 (CONT)
000 000 000 000 000 001 000 000 000 000 000 000 000 000 000 000 020 000 020 000 020 000 020 000 020 000 020 000 020 001 000
001 000 001 000 001 001 000 Mar 27/15 Mar 15/95 Jun 15/89 Jun 15/89 Mar 15/95 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Mar 15/95 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Aug 20/08 Sep 07/90 Sep 07/01 Mar 15/95 Feb 17/11 Feb 17/11 Nov 03/00 Nov 03/00 Feb 17/11 SECTION 6
3.5 3.6 3.7 3.8 3.9 3.10 3.11

4 4.1 4.2 4.3 4.4 4.5 4.5A 4.6 4.7 4.8 4.9 4.10 4.11 4.12 4.13 4.14 4.15 4.16 4.16A 4.17 4.17A 4.18 4.19 4.19 4.20 4.21 4.21 4.22 4.23 (CONT)
001 000 000 000 001 001 001
001 000 001 001 001 000 000 001 001 001 001 001 001 001 001 000 001 000 000 001 001 001 001 021 000 000 020 000 000 Mar 15/02 Oct 16/96 Mar 15/95 Mar 15/95 Mar 15/95 Mar 15/95 Mar 15/95
Nov 10/04 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Dec 05/03 Jun 15/89 Jun 15/89 Jun 15/89 Nov 14/89 Jun 15/89 Jun 15/89 Jun 15/89 Mar 12/99 Jun 15/89 Feb 17/11 Sep 07/01 Sep 07/01 Feb 17/11 Feb 17/11 Nov 10/04 Nov 10/04 Nov 10/04 Feb 17/11 Feb 17/11 Feb 17/11 Nov 10/04 Nov 10/04 SECTION 6
5 5.1 5.2 5.3 5.4 5.5 5.5A 5.6 5.7 5.8 5.9 5.10 5.11 5.12 5.13 5.14 5.15 5.16 5.16A 5.17 5.17A
6 6.1 6.2 6.3 6.4 6.5 6.5A 6.6 6.7 6.8 6.9 6.10 6.11 6.12 6.13 6.14 6.15 6.15A (CONT)
001 000 001 001 001 000 000 001 001 001 001 001 001 001 000 001 001 000 000 001 001
001 000 001 001 001 000 000 001 001 001 001 001 001 000 000 001 000 000 Nov 01/96 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Dec 05/03 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Feb 17/11 Sep 07/01 Sep 07/01 Feb 17/11 Feb 17/11
Nov 01/96 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Dec 05/03 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Feb 17/11 Sep 07/01 Sep 07/01

EASA Approved Mar 27/15

### Airplane Flight Manual GENERAL

AFM 340B Page 1- 6 Code 001 

### LIST OF EFFECTIVE PAGES (Cont’d)

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

SECTION 6
6.16 6.16A

7 7.1 7.2 7.3 7.4 7.5 7.5A 7.6 7.7 7.8 7.9 7.10 7.11 7.12 7.13 7.14 7.15 7.16 7.16A 7.17 7.17A
8 8.1 8.2 8.3 8.3 8.4 8.4 8.5 8.6 8.7 8.7 8.8 8.8 (CONT)
001 001
001 000 001 001 001 000 000 001 001 001 001 001 001 001 000 000 001 000 000 001 001
000 001 000 000 020 000 020 000 000 000 020 000 020 Feb 17/11 Feb 17/11
Nov 01/96 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Dec 05/03 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Jun 15/89 Feb 17/11 Sep 07/01 Sep 07/01 Feb 17/11 Feb 17/11
Jun 15/89 Feb 17/11 Feb 17/11 Nov 03/00 Feb 09/01 Feb 17/11 Feb 17/11 Nov 03/00 Nov 03/00 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 SECTION 6
9 9.1 9.2 9.3 9.3 9.3A 9.3A 9.4 9.4 9.5 9.5 9.6 9.6 9.6A 9.6A 9.7 9.7 9.8 9.8 9.9
10 10.1 10.2 10.3 10.3 10.3A 10.3A 10.4 10.4 10.5 10.5 10.6 10.6 (CONT)
000 001 001 000 020 000 020 000 020 000 020 000 020 000 020 000 020 000 020 001
000 001 001 000 020 000 020 000 020 000 020 000 020 Oct 16/96 Feb 17/11 Nov 30/07 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Feb 17/11 Feb 17/11 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Feb 17/11 Feb 17/11 Nov 03/00 Feb 09/01 Nov 30/07
Oct 16/96 Feb 17/11 Nov 30/07 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 Feb 17/11 Feb 17/11 Nov 03/00 Feb 09/01 Nov 03/00 Feb 09/01 SECTION 6
10.6A 10.6A 10.7 10.7 10.8 10.8 10.9
11 11.1 11.2 11.3 11.4 11.5
12 12.1 12.2 12.3 12.4 12.5

SECTION 7
SUPPLEMENTS

SECTION 8
APPENDICES (CONT)

000 020 000 020 000 020 001
001 001 000 000 001 001
000 000 000 000 000 000 Nov 03/00 Feb 09/01 Feb 17/11 Feb 17/11 Nov 03/00 Feb 09/01 Nov 30/07
Jun 15/89 Jun 15/89 Jun 15/89 Mar 15/95 Jun 15/89 Jun 15/89
Feb 26/10 Mar 15/95 Feb 26/10 Feb 26/10 Feb 25/05 Jan 17/90

EASA Approved Mar 27/15

### LIMITATIONS Airplane Flight Manual

AFM 340B Page 2- 9 Code 000 

### 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 o F). 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.

EASA Approved Mar 27/15These speeds already include an increment for maneuvering up to 30 degrees of bank. 

### LIMITATIONS Airplane Flight Manual

AFM 340B Page 2- 15 Code 000 

### AIRSPEEDS (Cont’d)

MINIMUM AIRSPEEDS FOR ICING CONDITIONS The minimum airspeeds below must be used for operation in icing conditions and, with Mod. No 3529 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 +15) 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 +15) 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” (VCLEAN +15).

............ For final approach: V REF +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

AFM 340B Page 2

− 16 Code 001 

### 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

.

−Minimum Use Heights (MUH):

 During take

− off or go

− around: 200 ft AGL (Above Ground Level)

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

−trim the aircraft before re

− engagement of the autopilot.
Yaw Damper Yaw Damper Operation is notauthorised 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

### LIMITATIONS Airplane Flight Manual

AFM 340B Page 2

− 17 Code 000 

### SYSTEMS (cont’d) Vertical Navigation The vertical guidance mode of the VNI 80 A when installed, is not certified for use as a primary source for vertical navigation. Cargo Fire The cargo compartment is classified as a Class C cargo compartment and has been demonstrated to provide the following minimum fire protection duration, based on cargo compartment configuration and fire protection system installation:

−70 min for aircraft with lavatory aft and Mod. No. 1149 incorporated (2 bottles)

−60 min for aircraft with lavatory forward and Mod. No.1149 incorporated (2 bottles)

−35 min for all other aircraft.

Cargo/Passenger configuration No passenger may be carried with the aircraft in cargo configuration.

Attitude/Heading Reference System During initialization on ground the aircraft must not be moved. Take

− off is not permitted:

−if attitude difference between the attitude displayed on both EFIS EADIs and the standby attitude indicator is

3 degrees or more (bank and pitch)

−if the heading on the compass card is slewing away from the aircraft heading.

Terrain Awareness and Warning System (TAWS) Navigation is not to be predicated on the use of the Terrain (or Obstacle) Awareness Display. NOTE The Terrain Awareness Display is intended to serve as a situational awareness tool only. It does not have the integrity, accuracy or fidelity on which to solely base decisions for terrain or obstacle avoidance.To avoid giving nuisance alerts, the predictive TAWS functions must be inhibited by selecting the TERR INHIBIT button when within 15 nm of take

− off, approach or landing at an airport that is not included in the airport database. Refer to Honeywell document 060

− 4326

− 000 for airports contained in the installed TAWS Terrain Database. The TAWS Pilot’s Guide (060

− 4314

− 000, dated April 2000, or later version) or equivalent TAWS description (e.g. AOM description) shall be carried on board and be immediately available to the crew.

cont’d...
EASA Approved Mar 27/15

### ABNORMAL PROCEDURES Airplane Flight Manual

AFM 340B Page 4

− 4 Code 001 

### 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 V REF20+10 KIAS or Flaps 35 and V REF35+ 10 KIAS Stabilizer fault, or Wing and stabilizer fault: Flaps 20 and V REF20+ 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 V REF20+ 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 GENERAL DATA 

### Airplane Flight Manual

AFM 340B Page 6- 2.11 Code 000 

### WIND COMPONENTS 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 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

AFM 340B Section 7 Code 001 EASA Approved Mar 27/15 

### LIST OF SUPPLEMENTS APPLICABLE TO DOC. NO AFM 340 B 001 The following Supplements 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.

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 10 Operation with Autocoarsen system i noperative 3 Mar 12/99 13 Traffic alert and Collision Avoidance System (TCAS II) 8 Dec 15/14 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 20 Steep Approach Operation 3 Feb 25/05 21 31 000 ft Ferry Operation * 3 Feb 17/11 24 ITT Exceedance during take- off or go- around 2 Oct 16/96 33 RAI Operation (Italy)* 1 Oct 16/96 38 High Altitude Airfield Performance 5 Feb 17/11 40 Operation with Increased Take- off Speeds 6 Feb 17/11 41 Operation from Unpaved/Gravel runways (FAA) 3 Feb 17/11 48 Extended operation with JP- 4 fuel* 1 Feb 27/98 55 Landing with tailwind above 10 knots* 1 Feb 20/12 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

AFM 340B Section 8 Code 001 

### LIST OF APPENDICES APPLICABLE TO AFM 340B 001 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 Reduced Take- off Power (FAA version) 4 Nov 03/00 Operation with Derated Power on the CT7- 9B Engine (FAA) 5 Feb 17/11 Operation with Derated Power on the CT7- 9B, Simplified method 7 Dec 05/03 Unbalanced Take- off Performance (FAA version) 4 Nov 22/13 Simplified Reduced Power Take- off 3 May 22/06

EASA Approved Mar 27/15