2015- 07- 03 Saab Aircraft AB Matilda Krig OFIC- 0

2015- 07- 03

Saab Aircraft AB

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Matilda Krig

OFIC- 0- 2015- 0003

Saab AB, Aeronautics

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

Postal address

Saab Aircraft ABTelephone Telefax

Nat 013 - 18 20 00

SWEDEN

Nat 013 - 18 44 95Saab AB

(2)

To: All holders of an Airplane Flight Manual AFM 340 A, code 001.

Subject: Revision No. 57 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 - ” - .

1- 8 000 Modification No. 1793 added.

1- 9 001 Modification No. 2905 moved from page 1- 8 (code 000).

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

2- 16 101 - ”- .

2- 16 201 - ”- .

2- 17 000 Page shift.

4- 1 000 Editorial.


4- 5 000 Deleted.

4- 5 001 New page unique to the Code 001 AFM.AOM Alert Operations Bulletin (AOB) No. 23 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. Recentlyan event with a ruptured de- ice boot resulted in slight vibrations starting at a speed ofapproximately 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 20resulted in a repetitive nose down pitch every 3 to 4 seconds together with rumbling andshaking of the flight controls.The nose down pitch was counteracted by pilot input and a go- around was initiated. Theaircraft 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 - indicatinga faulty STAB boot system - be experienced during flight, the landing shall be performedas a flap 0 landing.


6- 2.11 000 A parenthesis added to clarify that the demonstrated crosswind values include gust.

Cont’d…

Saab Aircraft ABSaab AB, Saab Aerosystems

Page 1 (2)

Cont’d…

REVISIONS TO SUPPLEMENTSList of Supplements Date changed to reflect this revision.

REVISIONS TO APPENDICESList of Appendices Date changed to reflect this revision.

With kind regards,Saab AB

Matilda Krig

Airplane Flight ManualIncluding SAAB- FAIRCHILD 340 A

RECORD OF REVISIONS - AFM 340A 001

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RECORD OF REVISIONS - AFM 340A 001

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GENERAL

AFM 340A Page 1- 4Code 001

LIST OF EFFECTIVE PAGES

The following pages comprise the Airplane Flight Manual for SAAB SF340A and SAAB- FAIRCHILD 340Aairplanes, whose registration authority accepts/approves the use of the U.S. Federal Aviation Administrationstandard version manual for flight operations.

REVISION No. 57 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.

NOTE1. Annotation after page number - refer to modification standard. (Detailed on Page 1- 7).

PAGE CODE DATE PAGE CODE DATE PAGE CODE DATE

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

EASA Approved Mar 27/15


GENERAL


LIST OF EFFECTIVE PAGES (Cont’d)


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SUPPLEMENTS

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APPENDICES

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GENERAL


LIST OF OPTIONS AND MODIFICATIONS QUOTED IN THIS MANUAL

Mod. No. Service Bulletin Subject

1067 SF340- 25- 007 Installation of improved observer’s seat.

1149 SF340- 26- 005 Cargo compartment, dual extinguisher bottles installed.

1150 SF340- 32- 011 Nose gear door linkage.. . . . . .

1198 SF340- 53- 005 Ditching capability (structural).

1212 SF340- 22- 006 Autopilot update - 1.

1213 SF340- 22- 007 Autopilot update - 2.

1222 SF340- 32- 018 MLG wheel seal. Wheel Assembly No 5007218.

1335 SF340- 30- 016 Prop de- ice, timing.

1339 SF340- 31- 010 Digital flight data recorder operation on ground.

1359 SF340- 34- 030 Improved pre- selector alert.

1380 SF340- 34- 032 Improved pre- selector alert.

1414 SF340- 74- 004 Introduction of Auto Ignition System.

1450 SF340- 79- 008 Introduction of an additional pressure switch to the power unit oilpressure indication system.

1462 SF340- 55- 008 New leading edge on horizontal stabilizer/upspring and in thebulletin listed modification (Mod. No. 1784) required for use of morethan 20 of flaps.

1463 SF340- 32- 030 Landing Gear extension and retraction, deletion of check valve function .

1468 SF340- 33- 019 Flashing beacon as replacement for rotating beacon.

1491 SF340- 61- 015 Activation of autocoarsening switcher units.

1492 SF340- 79- 009 Introduction of an additional pressure switch to the PGB pressureindication system.

1527 SF340- 39- 007 New CTOT panel with replacement of friction lock by detents.

1531 SF340- 32- 039 New Pivot Pin on NLG and all other in the bulletin listed modifications(Mod No 1762, 1763 and 1764) required for increased MTOW.

1783 SF340- 29- 004 Main accumulator low pressure warning.

1793 Saab340- 55- 010 Stabilizers - Removal of customer option (removal of up- droop stabilizer(Mod. No. 1462) to original stabilizer which means a maximum allowedflap setting of 20 degrees).

1933 Saab 340- 30- 031 Ice advisory system (ice detector).

2456 Saab 340- 34- 088 Radio altimeter AID strapping.

2558 Saab 340- 76- 032 Automatic Flight Idle Stop.

2674 Saab 340- 51- 013 Gravel runway protection.

2766 Saab 340- 34- 102 Flight Management System (Universal UNS- 1Msp)

LFV Approved Mar 27/15


GENERAL


LIST OF OPTIONS AND MODIFICATIONS QUOTED IN THIS MANUAL (CONT’D...)

Mod. No. Service Bulletin Subject

2905 Saab 340- 34- 106 Flight Management System (Universal UNS- 1K)combined with Collins Nav equipment.

2906 Saab 340- 34- 107 Flight Management System (Universal UNS- 1K)combined with King Nav equipment.

3034 Saab 340- 34- 136 Activation of the Non Precision Approach function.

3110 Saab 340- 25- 282 Introduction of a reinforced door installation to the flight compartment.

3168 Saab 340- 30- 089 Improved Ice Detector

3266 Saab 340- 34- 197 Flight Management System (Universal UNS- 1K+ and UNS- 1L).

3281 Saab 340- 34- 200 Flight Management System (Universal UNS- 1Lw).

3529 Saab 340- 27- 121 Flight Controls - Stall Warning/identification system - Activation ofimproved stall warning system for icing condition.



LIMITATIONS


OIL SYSTEM

Approved types of oil (engine and propeller gearbox)

Type I oils: Type II oils:BP Turbo Oil 2389 Aero Shell Turbine Oil 500ETO 2389 Castrol 205Exxon Turbo Oil 2389 BP Turbo Oil 2380Castrol 325 ETO 2380

Exxon Turbo Oil 2380Mobil Jet IIStauffer Jet II

Approved types of oil (engine only)

Type I oils: Type II oils:Mobil Jet 254

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

NOTE1. 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 allflight conditions.

Fuel anti- ice additives meeting specification Mil 27686E are authorized for use.Concentration shall be 0.06 % min to 0.15 % max by volume.

cont’d...


These speeds already include an incrementfor maneuvering up to 30 degrees of bank.


LIMITATIONS


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, holdingand 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 airframeandpropeller ice” (VCLEAN +15) may also be used for flaps 0 climb.

For single- engine climb after transitioning to the Enroute Climb configuration (after initial powerreduction from Take- off power) and for driftdown:

Flaps 0 “Enroute Climb Speed - with residual airframe and propeller ice” (VCLEAN +15).. . . . . . . . . . . .

For final approach:

VREF +10

Increase landing distance for the 10- knot speed increment applied to the reference speed in accordance withthe 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 aboveminimum sector altitude (MSA), then the speeds specified above.


Airplane Flight ManualIncluding SAAB−FAIRCHILD 340 A

LIMITATIONS

AFM 340A Page 2−16Code 001

SYSTEMSCabin Pressurization

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

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

Oxygen

Minimum crew oxygen for protective breathing is 800 psi.

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 directorlimitations, if the flight director and/or autopilot are engaged in a vertical mode during climb, IAS mode mustbe 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 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 toa maximum altitude of 14000 ft.

− Use of more than 20 degrees of flaps requires Mod. No. 1462 to be installed.

− 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 notilluminating, Flaps 0 must be used for landing (required by AD). For landing procedure see Section 4 AbnormalProcedures, Ice Protection Fault.

Stall protection

The stall protection system must be operative for take−off.

cont’d....



LIMITATIONS

AFM 340A Code 101 Page 2−16




Oxygen


Flight Director


Autopilot


− Autopilot operations is not authorised for coupled ILS approach.


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


Yaw Damper


− Take−off

− Go around

− Landing.

Flaps





Stall protection


cont’d....



LIMITATIONS





Oxygen


Flight Director


Autopilot


− Autopilot operations is not authorised for coupled ILS approach.


� 1000 ft AGL (Above Ground Level)


Yaw Damper


− Take−off

− Go around

− Landing.

Flaps





Stall protection


cont’d....



LIMITATIONS


SYSTEMS (cont’d)Vertical Navigation

The vertical guidance mode of the VNI 80 A, if installed, is not certified for use as a primary source for verticalnavigation.

Cargo Fire

The cargo compartment is classified as a Class C cargo compartment and has been demonstrated to providethe following minimum fire protection duration, based on cargo compartment configuration and fire protectionsystem 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.

Attitude/Heading Reference System

During initialization on ground the aircraft must not be moved.

Take−off is not permitted:

− until 2 minutes after initialization is completed

− if attitude difference between the attitude displayed on both EFIS EADIs and the standby attitude indicator is3 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.

NOTEThe Terrain Awareness Display is intended to serve as a situational awareness tool only. It does nothave the integrity, accuracy or fidelity on which to solely base decisions for terrain or obstacle avoid-ance.

To avoid giving nuisance alerts, the predictive TAWS functions must be inhibited by selecting the TERR IN-HIBIT button when within 15 nm of take−off, approach or landing at an airport that is not included in the airportdatabase. Refer to Honeywell document 060−4326−000 for airports contained in the installed TAWS TerrainDatabase.

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....



ABNORMAL PROCEDURES


TABLE OF CONTENTS

PAGE

GENERAL 4−2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BLEED AIR LEAK 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

LOSS OF BOTH BLEED SUPPLIES 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AVIONICS VENTILATION FAULT 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

DC GENERATOR FAULT 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

BATTERY FAULT 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PITCH TRIM SYNC FAULT 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

FLAP FAULT 4−3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

RUDDER LIMITER LIGHT ON 4−4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

HYDRAULIC WARNING 4−4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AC GENERATOR FAULT 4−4. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ICE PROTECTION SYSTEM FAULT 4−5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ALTERNATE EXTENSION OF LANDING GEAR 4−5. . . . . . . . . . . . . . . . . . . . . . . . . .

ANTI−SKID INOPERATIVE 4−5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

SINGLE ENGINE LANDING 4−5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

OIL BYPASS 4−5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

CHIP INDICATION 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

UNCOMMANDED ENGINE OPERATION 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

ENGINE TRQ AND/OR TEMP OVER LIMIT 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PROP RPM OVER LIMIT 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

AUTOCOARSEN FAULT 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .

PROPELLER BRAKE (if installed) 4−6. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .



ABNORMAL PROCEDURES


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 limiterswitch to OVERRIDE. Max speed with the rudder limiter in OVERRIDE is 180 KIAS. Avoid large rudder deflec-tions above 150 KIAS. If rudder limiter light is on below 140 KIAS, use if possible a runway with less than 10 ktscrosswind 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 suitableairport. Leave flaps in present position; use hand pump if brake pressure needs to be restored.

WITH MOD No. 1463 installed:

− If only emergency pressure is 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, switchbetween OVERRIDE and OFF so as to maintain pressure. If there is no increase in pressure duringoverride, switch off the pump and use 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.

WITHOUT MOD No. 1463 installed:

− If only emergency pressure is 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.

AC GENERATOR FAULT

Try to reset the generator once. If it will not reset, place the generator switch in OFF/R position and, if possible,exit icing conditions.



ABNORMAL PROCEDURES


ICE PROTECTION SYSTEM FAULT

Reset affected switch once. If the airframe or powerplant de−icing/anti−icing system is not restored, exit theicing conditions if possible.

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

With Mod. No. 1462 installed: Without Mod. No. 1462 installed or with Mod. Nos. 1462 and 1793 installed:

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

Stabilizer fault, orWing andstabilizer fault: Flaps 20 and VREF20 + 10 KIAS Flaps 0 and VREF20 + 30 KIAS

During landing with Master Caution (ICE PROT) and TIMER light illuminated and green STAB light notilluminating, use the following flap settings and speeds (required by AD) :

With Mod. No. 1462 installed: Without Mod. No. 1462 installed or with Mod. Nos. 1462 and 1793 installed:

Flaps 0 and VREF20 + 30 KIAS Flaps 0 and VREF20 + 30 KIAS

ALTERNATE EXTENSION OF LANDING GEAR(WITH MOD No. 1463 INSTALLED)

Select landing gear down and use the hand pump to extend the landing gear. Hand pump selector must be setto LDG GR position.

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

ANTI−SKID INOPERATIVE

CAUTIONUse of wheel brakes above 40 knots without anti−skid will likely result in flat tire(s).

Avoid braking until speed has decreased to 40 knots (on long runways, use reverse thrust as far as possible toavoid braking). Review landing performance, as the delayed use of brakes increases the landing distance asfor a ”very low friction runway” (aircraft braking � 0.05).

SINGLE ENGINE LANDINGUse Flaps 20 and VREF20 + 10 KIAS. Switch off the bleed system on approach.

OIL BYPASSIf engine oil pressure is within limits, continue normal operation monitoring oil pressure.



ABNORMAL PROCEDURES


CHIP INDICATIONReduce power and monitor engine instruments. If engine parameters deviate from normal, consider shuttingdown the engine.

UNCOMMANDED ENGINE OPERATION

NOTESmall TRQ indicator fluctuations (max 3%) in the form of oscillations or minor movements repeatedlyare acceptable if the fluctuations disappear after a Power Lever (Ng) or Condition Lever (Np) adjustment. Larger or uncontrollable fluctuations are to be considered as uncommanded engine operation, to be handledas below.

Uncommanded engine operation may be caused by sensor failure, electrical control failure or mechanical fail-ure.

The failure may create actual variations in power (increase and/or decrease in TRQ, ITT, Ng, PRPM andFuel Flow).

The failure may also be indicated on the cockpit indicators only, without any actual variations in power.

Uncommanded engine operation may affect aircraft controllability both in the air and on the ground e.g. duringtakeoff or during landing, depending on the cause of the condition.

In all cases of an UNCOMMANDED ENGINE OPERATION the Torque Motor must be locked out immedi-ately and the Autocoarsen System set to OFF.

If actual power variations continue after the Torque Motor has been locked out, consider shutdown of theaffected engine.

ENGINE TRQ AND/OR TEMP OVER LIMIT

Reduce power. If engine does not respond, shut down the engine.

PROP RPM OVER LIMIT

Set the propeller sync switch to OFF and retard the condition lever. If the propeller does not respond, shutdown the engine.

AUTOCOARSEN FAULT

Set the autocoarsen switch to OFF. Use a minimum VREF of 111 KIAS.

NOTEThis procedure does not preclude dispatch in accordance with the MMEL.

PROPELLER BRAKE (if installed)

If hydraulic warning light comes on with the propeller brake engaged, shut down the engine.



PERFORMANCEDEFINITIONS AND

GENERAL DATA

AFM 340A Page 6- 2.11Code 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 knotsthe headwind component is 26.8 knots



SUPPLEMENTS

AFM 340A Section 7Code 001

LIST OF SUPPLEMENTS APPLICABLE TO DOC. NO AFM 340 A 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 LatestRevision

Approvaldate

2 Operation above 25 000 ft. 8 Feb 17/11

4 Ferry Flight Kit P/N 7292199- 501 installed.* 1 Oct 18/96

8 CAT II Operation 12 Feb 17/11

10 CTOT Inoperative 4 Feb 17/11

11 Cargo/Passenger Configuration 3 Oct 18/96

13 Operation with Bottoming Governor Switches installed 3 Oct 18/96

18 Operation with Autocoarsen System Inoperative 5 Feb 17/11

21 Traffic alert and Collision Avoidance System (TCAS II) 6 Dec 15/14

23 Steep Approach operation 2 Feb 25/05

24 GPS Ferry Flight Kit 1 Oct 18/96

25 HF COM Ferry Flight Kit 1 Oct 18/96

27 RAI Operation (Italy)* 1 Oct 18/96

31 Extended operation with JP- 4 fuel* First Issue Mar 13/98

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

35 Cargo configuration 1 Jan 31/03

36 Increased Maximum Takeoff Weight (MTOW) 2 Aug 20/08

37 P- RNAV Operation* 3 Aug 14/14

* Distribution limited to particular operators.



APPENDICES

AFM 340A Section 8Code 001

LIST OF APPENDICES APPLICABLE TO AFM 340A 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 LatestRevision

Approvaldate

Configuration Deviation List 9 Nov 22/13

Operation with Reduced Take- off Power 11 May 22/06

Operation with Derated Power 7 Feb 17/11

Unbalanced Take- off Performance (FAA) 4 Nov 22/13

Simplified Derivative Engine Take- off Rating 3 May 22/06

Simplified Reduced Power Take- off 4 May 22/06


2015- 07- 03 Saab Aircraft AB Matilda Krig OFIC- 0

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Transcript of 2015- 07- 03 Saab Aircraft AB Matilda Krig OFIC- 0