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REV. 2, Date May/15/2011

IN ACCORDANCE WITH:

FAA MMEL SAAB 340B

REV. 17, DATE FEB/28/2011

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MMEL REV. No. 16

DATE: 05/06/2009 AEROLINEAS SOSA

MINIMUM EQUIPMENT LIST

ALS REV: Original

DATE: 11/13/2009

PAGE: COVER

RECORD AND CONTROL OF MANUAL

This Manual is the property of AEROLINEAS SOSA and is issued to the person mentioned

below. Under termination of employment it must be returned to the Director of

Maintenance.

NAME: ________________________________________

POSITION: ______________________________________

STATION: _______________________________________

COPY No. ________________________________________

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PAGE: I

TABLE OF CONTENTS

SYSTEM NO. SYSTEM PAGE-- Cover ---- Table of Contents I, II-- Control Page III, IV, V, VI, VII, VIII-- Log of Revisions IX, X-- Highlights of Change XI, XII, XIII, XIV, XV, XVI-- Distribution XVII, XVIII-- Company Procedures XIX, XX, XXI, XXII-- Definitions XXIII, XXVI, XXV, XXVI, XXVII, XXVIII-- Preamble XXIX, XXX-- Guidelines for (O) & (M) Procedures 1 through 4421 Air Conditioning 21-1 through 622 Auto Flight 22-1, 223 Communications 23-1,through 424 Electrical Power 24-1 through 425 Equipment/Furnishings 25-1 through 626 Fire Protection 26-1, 227 Flight Controls 27-1 through 428 Fuel 28-1 through 429 Hydraulic Power 29-1, 230 Ice and Rain Protection 30-1 through 731 Indicating/Recording Systems 31-1, 2, 332 Landing Gear 32-1 through 733 Lights 33-1 through 434 Navigation 34-1 through 1035 Oxygen 35-1, 236 Pneumatic 36-1, through 638 Water/Waste 38-149 Airborne Auxiliary Power 49-152 Doors 52-1, 256 Windows 56-1, 261 Propellers 61-1, 273 Engine Fuel & Controls 73-1, 274 Ignition 74-1, 275 Bleed Air 75-1, 276 Engine Controls 76-1, 277 Engine Indicating 77-1, 279 Engine Oil 79-1, 2100 Nonessential Equipment and Furnishing

Program (NEF Program) 1 through 18

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LOG OF REVISIONS

REVISION

No.

ISSUE

DATE

INSERTION

DATE

INSERTED

BY

AFFECTED

PAGES

1 Aug-04-2010 Aug-05-2010 Tech Pub. XXIV1 Aug-04-2010 Aug-05-2010 Tech Pub. 25-42 May-15-2011 May-16-2011 I. Betancourt I, III, IV, V, VI,

VII, IX, XI2 May-15-2011 May-20-2011 I. Betancourt 10, 12, 14, 392 May-15-2011 May-20-2011 I. Betancourt 21-1, 4, 5, 62 May-15-2011 May-20-2011 I. Betancourt 22-12 May-15-2011 May-20-2011 I. Betancourt 23-2, 3, 4

2 May-15-2011 May-20-2011 I. Betancourt 24-32 May-15-2011 May-20-2011 I. Betancourt 25-1. 2. 3. 4. 5.

62 May-15-2011 May-20-2011 I. Betancourt 26-1, 22 May-15-2011 May-20-2011 I. Betancourt 27-1, 22 May-15-2011 May-20-2011 I. Betancourt 28-1, 22 May-15-2011 May-20-2011 I. Betancourt 29-1, 22 May-15-2011 May-20-2011 I. Betancourt 30-4, 5, 62 May-15-2011 May-20-2011 I. Betancourt 31-1, 2, 32 May-15-2011 May-20-2011 I. Betancourt 32-1, 2, 3, 4, 5,

62 May-15-2011 May-20-2011 I. Betancourt 33-1, 32 May-15-2011 May-20-2011 I. Betancourt 34-1, 2, 3, 6, 7,

102 May-15-2011 May-20-2011 I. Betancourt 36-62 May-15-2011 May-20-2011 I. Betancourt 38-12 May-15-2011 May-20-2011 I. Betancourt 52-12 May-15-2011 May-20-2011 I. Betancourt 56-1

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HIGHLIGHTS OF CHANGEDESCRITPION TITLE SECTION PAGES

21-20-1 Recirculation Fans Proviso “b)” Recirculation Fancorrected to singular. Added newsub-item.

ATA 21 21-1

21-50-1 Air Conditioning Packs(Mod. 2305 installed)

Word order of proviso “f)” revised forclarity of intent.

ATA 21 21-4

21-60-1 Compressor/DuctOvertemperature (L/R DUCTOV TEMP) Caution Indicatorson Overhead Air ConditioningPanel (Mod. 2305 installed)

Word order of proviso “f)” revised forclarity of intent.

ATA 21 21-5

21-60-2 Cabin and Flight DeckAutomatic (AUTO) TemperatureControl Systems

Proviso “b)” Title of “CabinTemperature Indicator, and L DUCTTemperature Indicator (if installed)”corrected.

ATA 21 21-6

22-10-4 Autopilot Control WheelDisengage Switches

C/2/1 relief provisos amended IAWPolicy Letter P/L 93.

ATA 22 22-1

23-10-2 Selective Call System(s)(SELCAL)

In this case, item only applies to FAAMMEL. No change.

ATA 23 N/A

23-30-1 Passenger AddressSystem (PA)

Reformatted and amended IAWPolicy Letter P/L 9.

ATA 23 23-2

23-30-2 CrewmemberInterphone System(s)

Item number corrected to “23-30-2.”Reformatted and amended IAWPolicy Letter P/L 9.

ATA 23 23-2

23-50-3 Ground-to-CockpitIntercom System


ATA 23 23-4

23-50-4 Ground-To-CockpitIntercom System Chime


ATA 23 23-4

24-36-1 Battery VentilatingSystem

“(O)” added to denote that proviso“d)” necessitates development anduse of an alternate operationalprocedures to assure that affectedBattery (BAT) Switch(es) are selectedON prior to takeoff. Redundant word“prolonged” removed from proviso“d).”

ATA 24 24-3

24-37-1 Battery TemperatureIndicator

Number Installed corrected to “2.”Proviso “c)” amended to addclarification, “...on the associatedBattery...”

ATA 24 24-3

25-21-1 Flight Attendant SeatAssembly

Amended IAW Policy Letter P/L 97. ATA 25 25-1

25-21-3 Overhead StorageBin(s)/Cabin and GalleyStorage Compartment(s)/Closet(s)


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HIGHLIGHTS OF CHANGEDESCRITPION TITLE SECTION PAGES

25-23-10 Flight Deck DoorSurveillance System(s)

New Item added IAW Policy LetterP/L 122.

ATA 25 25-3

25-60-1 Emergency LocatorTransmitter (ELT)


25-60-2 Observer Seat(Including AssociatedEquipment.)

Previous proviso “a)” deleted fromsecond Proviso set. NOTE-1 - “isoperates” corrected to “operates.”

ATA 25 25-4

25-60-3 Passenger Seats Relief Category changed to “D” IAWPolicy Letter P/L 79. “Affected”added to proviso “b).” The word “to”added to NOTE 3 for clarity of intent.

ATA 25 25-4

25-60-3-1) Passenger Seats -Recline Mechanism(s)

In accordance with Policy letter P/L79: Relief Category changed to “D.”In first relief option, “affected SeatBacks,” and “full” added to clarifyintent. Second relief option added.

ATA 25 25-5

25-60-3-3) Passenger Seats –Armrests

Relief Category changed to “D,”and wording “full” added to bothprovisos “c)” to clarify required SeatBack position, IAW Policy Letter P/L79.

ATA 25 25-5

25-60-4 "Fasten Seat BeltWhile Seated" Signs andPlacards

Was corrected “Placards installed on‘B’ Seats…” by “Placards installed on‘C’ Seats… ”

ATA 25 25-5

25-60-5 Non-Essential

Equipment & Furnishings (NEF)

NOTE 2 – NOTE number corrected to

“2.” Extraneous “are” deleted.

ATA 25 25-5

25-60-8 Cargo Restraint Systems Amended IAW Policy Letter P/L 100. ATA 25 25-6

25-62-10 Emergency MedicalKit (EMK) and/or AssociatedEquipment

New Item added IAW Policy Letter73.

ATA 25 25-6

25-62-15 Automatic ExternalDefibrillator (AED) and/orAssociated Equipment

New Item added IAW Policy Letter73.

ATA 25 25-6

26-13-1 Lavatory SmokeDetection System

Amended IAW Policy Letter 24. ATA 26 26-1

26-22-1 Portable Fire

Extinguisher(s)

New Item added IAW Policy Letter

75.

ATA 26 26-2

26-22-2 Lavatory FireExtinguisher System


27-13-1 Aileron (ROLL) TrimIndicators

Provisos “a),” and “c),” “affected”added.

ATA 27 27-1

27-23-1 Rudder (YAW) TrimIndicator

Proviso clarified by adding wording“‘…is in the’ Neutral position.”

ATA 27 27-2

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HIGHLIGHTS OF CHANGE

DESCRITPION TITLE SECTION PAGES28-22-2 L/R STBY PRESS Lights Proviso “b),” “Associated” added. ATA 28 28-1

28-22-7 Standby Pump (STBYPUMP) Automatic ControlModes

Item Title and provisos corrected toplural; and Number Installedamended to “2.”

ATA 28 28-2

29-32-1 Cockpit Main (MAIN)Hydraulic Accumulator PressureIndication

Proviso “e),” “Accumulator” added. ATA 29 29-1

29-32-2 Cockpit Brake(OUTB/INBD) Hydraulic

Accumulator Press. Indications

Proviso “d),” “Accumulator” added. ATA 29 29-2

30-32-1 Pitot Heater CautionIndications (L PITOT, R PITOT,STBY PITOT)

NOTE added to B/3/2 reliefstatement to clarify that a Pitot HeatCaution Indication is not required ifthe associated Pitot Tube Heater isinoperative and deferred IAW theMEL.

ATA 30 30-4

30-34-1 OAT Probe Heater Proviso “a)” deleted. ATA 30 30-5

30-34-2 OAT Caution Indication Proviso “a)” deleted. ATA 30 30-6

31-30-1 Flight Data Recorder(FDR) System


31-50-2-1) Aural Alert System -T/O Inhibit Function

Reference for new Item corrected to“31-50-5.”

ATA 31 31-2

31-50-2-2) Aural Alert System -GND OP Function

Reference for new Item corrected to“31-50-6.”

ATA 31 31-2

31-50-4 Master Caution AuralAlert (Single Chime)

Item Number corrected to “31-50-4.” ATA 31 31-3

31-50-5 Takeoff Inhibit (T/O INH)System

Item number corrected to 31-50-5. ATA 31 31-3

31-50-6 Ground Operation(GND OP) System

Item number corrected to 31-50-6. ATA 31 31-3

32-31-1 Landing Gear HandleDownlock Latch Solenoid

Proviso “b),” Cautionary wordingamended to “…MUST NOT BETOUCHED.”

ATA 32 32-1

32-43-1-1)-a) Anti-Skid System -Airplanes w/o Wet RunwayPerformance Data (Saab-340A& Saab-340B without ExtendedWingtips) – Dry Runways

NOTE-1 Amended to, “WhenLanding Gear is retracted, theAmber FI STOP Caution Light willilluminate, and the Blue FI STOPStatus Light will remain illuminated.”

ATA 32 32-2

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DESCRITPION TITLE SECTION PAGES32-43-1-1)-b) Anti-Skid System -Airplanes w/o Wet RunwayPerformance Data (Saab-340A &Saab-340B without ExtendedWingtips) – Wet Runways (Nostanding water, snow, or icecontamination on takeoff orlanding runway)

Proviso “b)”corrected to “PropellerReverse.” NOTE-1 Amended to, “WhenLanding Gear is retracted, the Amber FISTOP Caution Light will illuminate, and theBlue FI STOP Status Light will remainilluminated.”

ATA 32 32-3, 32-4

32-43-2-1)-a) A-SKID INOP CautionIndication - Airplanes w/o Wet

Runway Performance Data(Saab-340A & Saab-340B withoutExtended Wingtips) – DryRunways

NOTE-1 Amended to, “When LandingGear is retracted, the Amber FI STOP

Caution Light will illuminate, and the BlueFI STOP Status Light will remainilluminated.”

ATA 32 32-5

32-43-2-1)-b) A-SKID INOP CautionIndication - Airplanes w/o WetRunway Performance Data(Saab-340A & Saab-340B withoutExtended Wingtips) – WetRunways (No standing water,snow, or ice contamination ontakeoff or landing runway)

Proviso “b)”corrected to “PropellerReverse.” NOTE-1 Amended to, “WhenLanding Gear is retracted, the Amber FISTOP Caution Light will illuminate, and theBlue FI STOP Status Light will remainilluminated.”

ATA 32 32-5, 32-6

33-20-2 Lighted PassengerInformation Signs (NoSmoking/Fasten Seat

Belt/Return to Seat Signs)


Rotating Beacons/ FlashingBeacons Flashing Beacon/Anti-Collision Lights (Mod. 1913installed)

Was corrected REMARKS IAW Mod. 1913installed.

ATA 33 33-3

33-44-1 Wing Inspection Lights IAW Policy Letter P/L 72, proviso added touse during night operations toaccount for possible use in associationwith Ground De-icing Procedures.

ATA 33 33-3

33-51-1 Cockpit EmergencyLighting System

Deleted, Revision 17, IAW Policy Letter 63,the MMEL/MEL Preamble, andoperational FAR’s permitting use of MEL’s.Normally operating Cockpit EmergencyLighting are considered necessary in

order for crews to be able to accomplishEmergency Procedures, such as Smoke inthe Cockpit, in day or night conditions.

ATA 33 33-3

34-11-2 Standby Pitot StaticSystem

Proviso added in consideration of theintent of Policy Letter P/L 111, prohibitingoperations in known or forecast over-the-top conditions. Associated NOTESrenumbered “1,” and “2.”

ATA 34 34-1, 34-2

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DESCRITPION TITLE SECTION PAGES34-12-5 AltitudeAlerting/Preselect System

Amended IAW latest version ofPolicy Letter 39.

ATA 34 34-3

34-24-1-4)-a) Electronic FlightInstrument Systems (EFIS) -Multifunction Display Unit (MFD)– Aircraft without Collins TCAS IIInstalled

This Item is N/A. MFD is not installedon A/C N366PX, MSN 267. Nochange.

ATA 34 N/A

34-24-1-4)-b) Electronic FlightInstrument Systems (EFIS) -

Multifunction Display Unit (MFD)– Aircraft with Collins TCAS IIInstalled

This Item is N/A. MFD is not installedon A/C N366PX, MSN 267. No

change.

ATA 34 N/A

34-24-1 Electronic FlightInstrument Systems (EFIS)

Was explicitly described the items 3),4), 7) and 8).

ATA 34 34-6

34-30-1 VHF NAV Systems(VOR/ILS)

Relief statement enhanced IAWintent of Policy Letter P/L 63.

ATA 34 34-7

34-44-1 Windshear AlertingSystem(s)

This Item is N/A. ‘WAS(s)’ is notinstalled on A/C N366PX, MSN 267.No change.

ATA 34 N/A

34-54-1 ATCTransponder/AutomaticAltitude Reporting System(s)

NOTE added to both Proviso sets;and, Number Installed corrected to“2”.

ATA 34 34-10

Item 34-54-1-1) ATCTransponder/AutomaticAltitude Reporting System(s) -Aircraft with two Mode STransponders installed

New Item for airplanes with two (2)Mode S Transponders installed. ATA 34 34-10

36-20-4 Cross Valve Open(XVALVE) Caution Indication

Number Installed correct to “1;” andNumber Required for Dispatchcorrected to “0.”

ATA 36 36-6

38-10-1 Potable WaterSystem(s)

Corrected to “NOT INSTALLED” ATA 38 38-1

52-70-1 External Door WarningSystem

Proviso “b)” amended withparenthetical reference “(CargoDoor & Cockpit Escape Hatch)”toclarify that these are the “Inward

Opening Access Doors”

ATA 52 52-1

56-10-1-1) Cockpit Windshieldsand Side Windows Outer PlySurfaces

Deleted IAW Policy Letter 124. NOTEadvises operators to refer toMaintenance Manual (AMM),Structural Repair Manual (SRM), orother Approved documentation.

ATA 56 56-1

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DISTRIBUTION

Each copy of this Minimum Equipment List will have a record and control of themanual in the cover page. The Director of Maintenance will keep it filed with therecords of manual holders.

Objective: The objective of distributing this Minimum Equipment list is that thepersonnel involved in the operation of the aircraft have a document for their useand guidance concerning the operation and maintenance procedures thatAerolíneas Sosa uses for deferring inoperative equipment.

Supplying: Only the Director of Maintenance has the authority to provide copiesof this Minimum Equipment List.

Accessibility: A copy of this minimum equipment list is kept in the maintenancetechnical library of the company and is available for all relevant personnel andany others whose duties are related to these procedures.

Actualization: The manual holder is responsible to insert the revision (s) in theminimum equipment list and to fill out the record of revisions of the manual. TheMEL onboard the aircraft will be updated by the Chief Pilot.

Verification: The Inspection personnel will verify that the Minimum Equipment Listsin use and onboard the aircraft are updated. For this reason they will carry outperiodic checks to confirm that all company Minimum Equipment Lists arecurrent.

NOTE: The partial or total redaction or copying of this Minimum Equipment List isnot allowed without authorization in writing from the Director of Maintenance.

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COMPANY PROCEDURES

RESPONSIBILITIES

The Federal Aviation Regulations allow for aircraft operation with certain items ofequipment inoperative using an approved Minimum Equipment List (FAR 129.14).

The Pilot in Command of an aircraft is directly responsible for, and is the finalauthority as to, the operation of the aircraft. It is his/her responsibility to assure that

the flight can be conducted safely with inoperative equipment and will follow theprocedures as per the aircraft approved MEL and the GOM. The flight crew will beresponsible for reviewing the maintenance logbook and to be aware of the statusof any discrepancies and to confirm the aircraft airworthiness status. The Pilot inCommand will seek guidance from the Director of Maintenance if necessary.

The Chief Pilot and the Director of Maintenance are jointly responsible for exercisingthe necessary operational control to ensure that an acceptable level of safety ismaintained.

Should any doubt exist as to the interpretation of MEL items, or the action to betaken, assistance shall be obtained from the Director of Maintenance, his/herdesignee, the Director of Operations or his/her designee.

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COMPANY PROCEDURESPROCEDURES

Prior to deferring an item the following must be considered:• An approved MEL for the aircraft exists.• There is an Aircraft Maintenance Logbook to enter the discrepancies and the

corrective actions.• The aircraft must be operated in accordance with the applicable conditions

and limitations in the MEL.

To defer an item:

1. When a discrepancy is discovered or equipment is inoperative, the MEL of theaircraft is consulted as to whether it is possible to enter the item as deferred,and to verify the limitations of operation or maintenance of the deferral.

2. The components numbered in the MEL are classified in four categories: A, B, Cand D, which determine the maximum time that a component can bedeferred. For the purpose of the MEL, any reference to time means “LOCALTIME”.

CATEGORY “A”. Any component numbered in the MEL in the category “A”,must be repaired in accordance with the time interval specified in the remarkcolumn of the MEL approved by the FAA.

CATEGORY “B”. The components of the MEL in category “B” are required to berepaired within Three (3) calendar days, excluding the day it was placarded.

CATEGORY “C”. The components of the MEL in category “C” are required tobe repaired within Ten (10) calendar days, excluding the day it wasplacarded.

CATEGORY “D”. The components of the MEL in category “D” are required tobe repair within One hundred and twenty (120) calendar days, excluding theday it was placarded.

3. After determining that the item can be deferred, the Pilot in command or theauthorized maintenance personnel will enter the discrepancy in the aircraftmaintenance logbook indicating the item, date, the MEL reference and thecategory of the deferral.

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COMPANY PROCEDURES

4. The person entering the item in the aircraft maintenance logbook will take allthe required actions in the MEL. When the maintenance personnel defers anitem they will follow the actions identified by an “M” if the Pilot is deferring theitem he will follow the actions identified with an “O”.

5. The maintenance personnel will follow the procedures for the MEL specified inthe General Maintenance Manual.

6. The pilot in command will follow the procedure for MEL specify in the GeneralOperations Manual. It is the responsibility of the Pilot in command to make adecision to continue the flight and to defer an item or to return the aircraft tothe station.

7. Maintenance personnel are responsible for the accomplishment of allmaintenance actions including system testing and securing inoperative items.If the flight is to be released with an inoperative item, it is the responsibility ofthe authorized maintenance technician to advise the pilot in command and tosign the aircraft airworthiness release.

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COMPANY PROCEDURES

DEFERRED REPORTS AWAY FROM BASE:

When some instrument or equipment fails away from the base, this can beentered as a deferral, according to the MEL.

The Captain of the aircraft must be in contact with the Maintenance Departmentof Aerolineas SOSA to plan a course of action. If the decision is to defer the item

the Captain will proceed to enter the deferred item in the aircraft maintenancelogbook and will follow the MEL procedure which includes installing the INOPsticker (Inoperative) on the instrument or equipment that has been deferred. Thissticker must be completed with the following data written on it: MEL referenceand the Date of entry.

In the Aircraft Maintenance Logbook the Captain must enter a report to indicatethat he/she placed the sticker as per the instructions of the Maintenancedepartment, so that it can be noted when arriving at the maintenance base, andthe report entered in the aircraft maintenance log, according to the procedures of the

GOM and GMM.

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DEFINITIONS

1. System Definitions.

System numbers are based on the Air Transport Association (ATA) SpecificationNumber 100 and items are numbered sequentially.

a. "Item" (Column 1) means the equipment, system, component, or function listedin the "Item" column.

b. "Number Installed" (Column 2) is the number (quantity) of items normally installedin the aircraft. This number represents the aircraft configuration considered indeveloping this MMEL. Should the number be a variable (e.g., passengercabin items) a number is not required.

c. "Number Required for Dispatch" (Column 3) is the minimum number (quantity) ofitems required for operation provided the conditions specified inColumn 4 are met.

NOTE: Where the MMEL shows a variable number required for dispatch, the MELmust reflect the actual number required for dispatch or an alternate means

of configuration control approved by the Administrator.

d. "Remarks or Exceptions" (Column 4) in this column includes a statement eitherprohibiting or permitting operation with a specific number of items inoperative,provisos (conditions and limitations) for such operation, and appropriatenotes.

e. A vertical bar (change bar) in the margin indicates a change, addition ordeletion in the adjacent text for the current revision of that page only. Thechange bar is dropped at the next revision of that page.

2. "Airplane/Rotorcraft Flight Manual" (AFM/RFM) is the document required for typecertification and approved by the responsible FAA Aircraft Certification Office. TheFAA approved AFM/RFM for the specific aircraft is listed on the applicable TypeCertificate Data Sheet.

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DEFINITIONS

3. Each inoperative item must be placarded to inform and remind the crewmembersand maintenance personnel of the equipment condition.

NOTE: To the extent practical, placards should be located adjacent to the control orindicator for the item affected; however, unless otherwise specified, placardwording and location will be determined by the operator.

4. "-" symbol in Column 2 and/or Column 3 indicates a variable number (quantity) ofthe item installed.

5. "Deleted" in the remarks column after a sequence item indicates that the item waspreviously listed but is now required to be operative if installed in the aircraft.

7. "ER" refers to extended range operations of a two-engine airplane which has a typedesign approval for ER operations and complies with the provisions of AdvisoryCircular 120-42A.

8. "Federal Aviation Regulations" (FAR) means the applicable portions of the Federal

Aviation Act and Federal Aviation Regulations.

9. "Flight Day" means a 24 hour period (from midnight to midnight) either UniversalCoordinated Time (UCT) or local time, as established by the operator, during whichat least one flight is initiated for the affected aircraft.

10. "Icing Conditions" means an atmospheric environment that may cause ice to formon the aircraft or in the engine(s).

11. Alphabetical symbol in Column 4 indicates a proviso (condition or limitation) thatmust be complied with for operation with the listed item inoperative.

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DEFINITIONS

12. "Inoperative" means a system and/or component malfunctions to the extent that itdoes not accomplish its intended purpose and/or is not consistently functioningnormally within its approved operating limit(s) or tolerance(s).

13. "Notes:" in Column 4 provides additional information for crewmember ormaintenance consideration. Notes are used to identify applicable material which isintended to assist with compliance, but do not relieve the operator of theresponsibility for compliance with all applicable requirements. Notes are not a partof the provisos.

14. Inoperative components of an inoperative system:Inoperative items which are components of a system which is inoperative areusually considered components directly associated with and having no otherfunction than to support that system. (Warning/caution systems associated with theinoperative system must be operative unless relief is specifically authorized per theMMEL).

15. "(M)" symbol indicates a requirement for a specific maintenance procedure which

must be accomplished prior to operation with the listed item inoperative. Normallythese procedures are accomplished by maintenance personnel; however, otherpersonnel may be qualified and authorized to perform certain functions.Procedures requiring specialized knowledge or skill, or requiring the use of tools ortest equipment should be accomplished by maintenance personnel. Thesatisfactory accomplishment of all maintenance procedures, regardless of whoperforms them, is the responsibility of the operator.Appropriate procedures are required to be published as part of the operator'smanual or MEL.

16. "(O)" symbol indicates a requirement for a specific operations procedure which

must be accomplished in planning for and/or operating with the listed iteminoperative. Normally these procedures are accomplished by the flight crew;however, other personnel may be qualified and authorized to perform certainfunctions. The satisfactory accomplishment of all procedures, regardless of whoperforms them, is the responsibility of the operator. Appropriate procedures arerequired to be published as a part of the operator's manual or MEL.

NOTE: The (M) and (O) symbols are required in the operator's MEL unless otherwiseauthorized by the Administrator.

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DEFINITIONS

17. "Deactivated" and "Secured" means that the specified component must be putinto an acceptable condition for safe flight. An acceptable method of securing ordeactivating will be established by the operator.

18. "Visual Flight Rules" (VFR) is as defined in FAR Part 91. This precludes a pilot from filingan Instrument Flight Rules (IFR) flight plan.

19. "Visual Meteorological Conditions" (VMC) means the atmospheric environment issuch that would allow a flight to proceed under the visual flight rules applicable to

the flight. This does not preclude operating under Instrument Flight Rules.

20. "Visible Moisture" means an atmospheric environment containing water in anyform that can be seen in natural or artificial light; for example, clouds, fog, rain,sleet, hail, or snow.

21. "Passenger Convenience Items" means those items related to passengerconvenience, comfort or entertainment such as, but not limited to, galleyequipment, movie equipment, ash trays, stereo equipment, overhead readinglamps, etc.

22. Repair Intervals: All users of an MEL approved under FAR 121, 125, 129 and 135must effect repairs of inoperative systems or components, deferred in accordancewith the MEL, at or prior to the repair times established by the following letterdesignators:

Category A. Items in this category shall be repaired within the time intervalspecified in the remarks column of the operator's approved MEL.

Category B. Items in this category shall be repaired within three (3) consecutivecalendar days (72 hours), excluding the day the malfunction was recorded in the

aircraft maintenance record/logbook.For example, if it were recorded at 10 a.m. on January 26th, the three day intervalwould begin at midnight the 26th and end at midnight the 29th.

Category C. Items in this category shall be repaired within ten (10) consecutivecalendar days (240 hours), excluding the day the malfunction was recorded in theaircraft maintenance record/logbook. For example, if it were recorded at 10 a.m.on January 26th, the 10 day interval would begin at midnight the 26th and end atmidnight February 5th.

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Category D. Items in this category shall be repaired within one hundred and twenty(120) consecutive calendar days (2880 hours), excluding the day the malfunctionwas recorded in the aircraft maintenance log and/or record.

The letter designators are inserted adjacent to Column 2.

23. "Day of Discovery" is the calendar day an equipment/instrument malfunction wasrecorded in the aircraft maintenance log and or record. This day is excluded fromthe calendar days or flight days specified in the MEL for the repair of aninoperative item of equipment. This provision is applicable to all MEL items, i.e.,categories "A, B, C, and D."

24. Nonessential Equipment and Furnishings (NEF) are those items installed on theaircraft as part of the original type certification, supplemental type certificate, orother form of alteration that have no effect on the safe operation of flight andwould not be required by the applicable certification rules or operational rules.They are those items that if inoperative, damaged or missing have no effect on theaircraft’s ability to be operated safely under all operational conditions. These

nonessential items may be installed in areas including, but not limited to, thepassenger compartment, flight deck area, service areas, cargo areas, crew restareas, lavatories, and galley areas. NEF items are not items already identified in theMEL or CDL of the applicable aircraft. They do not include items that arefunctionally required to meet the certification rule or for compliance with anyoperational rule. Operator’s NEF process shall not provide for deferral of itemswithin serviceable limits identified in the manufacture’s maintenance manual oroperator’s approved maintenance program such as wear limits, fuel/hydraulicleak rates, oil consumption, etc. Cosmetic items that are fully serviceable but wornor soiled may be deferred under an operator’s NEF process.

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BLANK INTENTIONALLY

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PREAMBLE

The following is applicable for AEROLINEAS SOSA operating under Federal AviationRegulations (FAR) Part 129: The FAR require that all equipment installed on anaircraft in compliance with the Airworthiness Standards and the Operating Rulesmust be operative. However, the Rules also permit the publication of a MinimumEquipment List (MEL) where compliance with certain equipment requirements isnot necessary in the interest of safety under all operating conditions. Experiencehas shown that with the various levels of redundancy designed into aircraft,operation of every system or installed component may not be necessary when theremaining operative equipment can provide an acceptable level of safety. AMaster Minimum Equipment List (MMEL), is developed by State Aviation Inspection,with participation by the aviation industry, to improve aircraft utilization andthereby provide more convenient and economic air transportation for the public.

This FAA approved MEL includes those items of equipment related to airworthiness

and operating regulations and other items of equipment which Aerolineas Sosa

finds may be inoperative and yet maintain an acceptable level of safety by

appropriate conditions and limitations; it does not contain obviously required items

such as wings, flaps, and rudders. The MMEL is the basis for development of ALS’

MEL, which takes into consideration ALS’ particular aircraft equipment

configurations and operational conditions.

ALS’ MEL for administrative control may include items not contained in the MMEL;

however, relief for administrative control items must be approved by the

Administrator. ALS’ MEL may differ in format from the MMEL, but cannot be less

restrictive than the MMEL. The individual ALS MEL, when approved and authorized,

permits operation of the aircraft with inoperative equipment.

Equipment not required by the operation being conducted, and equipment in

excess of FAR requirements, are included in the MEL with appropriate conditions

and limitations. The MEL must not deviate from the Aircraft Flight ManualLimitations, Emergency Procedures or with Airworthiness Directives. It is important to

remember that all equipment related to the airworthiness and the operating

regulations of the aircraft not listed on the MMEL must be operative. Suitable

conditions and limitations,

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in the from of placards, maintenance procedures, crew operating procedures andother restrictions, as necessary, are specified in the MEL to ensure that anacceptable level of safety is maintained.

The MEL is intended to permit operation with inoperative items of equipment for aperiod of time until repairs can be accomplished. It is important that repairs beaccomplished at the earliest opportunity. In order to maintain an acceptable levelof safety and reliability, the MEL establishes limitations on the duration of conditionsfor operation with inoperative equipment. The MEL provides for release of theaircraft for flight with inoperative equipment.

When an item of equipment is discovered to be inoperative, it is reported bymaking an entry in the aircraft Maintenance Record/Logbook as prescribed byFAR. Such documentation is required prior to operation with an item of equipmentinoperative.

ALS is responsible for exercising the necessary operational control to ensure that anacceptable level of safety is maintained. When operating with multiple inoperativeitems, the interrelationships between those items and the effect on the aircraft

operation and crew workload will be considered.

ALS has established a procedure in its General Maintenance Manual that includesthe parts, personnel, facilities, procedures, and schedules to ensure timely repair ina controlled and sound fashion.

WHEN USING THE MEL, COMPLIANCE WITH THE STATED INTENT OF THE PREAMBLE,DEFINITIONS, AND THE CONDITIONS AND LIMITATIONS SPECIFIED IN THE MEL ISREQUIRED.

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GUIDELINES FOR (O) & (M) PROCEDURES

ATA 21

k. Set the R HP VALVE switch to AUTO (AIR COND panel).– If hot temperature in the Cockpit:

l. Set the F DECK temp selector to COLD (AIR COND panel).Check for cold airflow from the Flightdeck Gaspers.– If cold temperature in the Cockpit:

m. Set the F DECK temp selector to HOT (AIR COND panel).Check for hot airflow from the Flightdeck Gaspers.

n. End of procedure.

20-3 (M) 1. Switch off optional equipment not required for safe operations, and notapplicable to operational navigation, by pulling the appropriate CircuitBreakers:

ACAS/TCAS (L–19)

1. Open the Avionics Door and check that the DPU Fans operate normally.a. Set the L and R BAT switch to ON (DC ELEC panel).b. Set the L and R AVION switch to ON (DC ELEC panel).

The DPU Fans can easily be heard but also physically feel for a coolairflow above the DPUs.

Remove the door if the cabin temperature is above +24 oC (+75 oF) toprevent possible rack overtemperature.

c. End of procedure.

(O) 1. Check that the Avionic Rack Fan operates normally.a. Set the L and R BAT switch to ON (DC ELEC panel).b. Set the right TEMP SELECT switch to neutral position (AIR COND panel).c. Set the ESS AVION switch to ON (DC ELEC panel).

– The fan can easily be heard and not to be mistaken of the sound fromthe Cockpit Temperature Sensor.

d. End of procedure.

OR

(Continued)

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ATA 21

2. Check that both Air Condition Packs operate normally.a. After engine start set the L RECIRC switch to ON (AIR COND panel).b. Set the R BLD VALVE switch to OFF (AIR COND panel).c. Set the L BLD VALVE switch to RESET/AUTO (AIR COND panel).d. Set the L HP VALVE switch to AUTO (AIR COND panel).

– If hot temperature in the Cabin:e. Set the CABIN temp selector to COLD (AIR COND panel).

Check for cold airflow from the Cabin Gaspers.– If cold temperature in the Cabin:

f. Set the CABIN temp selector to HOT (AIR COND panel).Check for hot airflow from the Cabin Gaspers.

g. Set the L RECIRC switch to OFF(AIR COND panel).h. Set the R RECIRC switch to ON (AIR COND panel).i. Set the L BLD VALVE switch to OFF (AIR COND panel). j. Set the R BLD VALVE switch to RESET/AUTO (AIR COND panel).k. Set the R HP VALVE switch to AUTO (AIR COND panel).

– If hot temperature in the Cockpit:l. Set the F DECK temp selector to COLD (AIR COND panel).

Check for cold airflow from the Flightdeck Gaspers.– If cold temperature in the Cockpit:

m. Set the F DECK temp selector to HOT (AIR COND panel).Check for hot airflow from the Flightdeck Gaspers.

n. End of procedure.

31-1 (M) 1. Removal of the Primary Outflow Valve. Procedure IAW SAAB 340 MELPG21-31-1. Rev. 10 – Dec/15/2006:

A. Pull and secure CB 1HB CAB PR CTL & EM DUMP (G–7) also CB 2HB CABINPRESS/AUTO DUMP (M–6).

B. Disconnect, tag, cap and secure the Outflow Valve electricalconnections.

(Continued)

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ATA 21

C. Disconnect, tag, cap and secure all hoses on the Outflow Valve.D. Release nut of T–bolt on coupling to remove coupling from Bulkhead

Flange.E. Pull out, remove and tag the Outflow Valve.F. Cap all the Valve Pressure Ports.G. Remove the Coupling.H. Remove and discard the O–ring from the groove in the Flange.I. Reset CB 2HB CABIN PRESS/AUTO DUMP (M–6).

J. Make appropriate entry in the aircraft log book.

(O) 1. Perform below check of the Automatic Pressurization Control System andPressure Dump System with both engines running in Flight Idle.A. Set the L+R BLD VALVE switch to RESET/AUTO (AIR COND panel).B. Set the L+R HP VALVE switch to AUTO (AIR COND panel).C. Set the MODE selector switch to AUTO (Center pedestal).D. Set the landing altitude to 1000 feet below the actual airport elevation

(Center pedestal).E. Set Barometric set knob to actual airfield pressure + 1.0 in HG (Center

pedestal).

F. Set the CAB PRESS test switch in up position (TEST 2 panel).G. Correct function of the Automatic Pressurization System is indicated by:

– An increase in DIFF PRESS (Max obtainable diff pressure is 0.4 – 0.5 psi).– CABIN ALT to decrease.

H. Set the PRESS DUMP switch to ON (EMERGENCY panel).– Correct function of Pressure Dump System is indicated by the diff.

pressure decreasing to 0.1+/– 0.3 psi.I. End of procedure.OR

2. The flight will be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).B. End of procedure.



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ATA 21


C. Disconnect, tag, cap and secure all hoses on the Outflow Valve.D. Release nut of T–bolt on coupling to remove coupling from bulkhead

flange.E. Pull out, remove and tag the Outflow Valve.F. Cap all the Valve Pressure Ports.

G. Remove the Coupling.H. Remove and discard the O–ring from the groove in the Flange.I. Reset CB 2HB CABIN PRESS/AUTO DUMP (M–6).J. Make appropriate entry in the aircraft log book.

(O) 1. The flight will be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).B. End of procedure.




C. Disconnect, tag, cap and secure all hoses on the Outflow Valve.D. Release nut of T–bolt on coupling to remove coupling from Bulkhead

Flange.E. Pull out, remove and tag the Outflow Valve.F. Cap all the Valve Pressure Ports.G. Remove the Coupling.H. Remove and discard the O–ring from the groove in the Flange.I. Reset CB 2HB CABIN PRESS/AUTO DUMP (M–6).J. Make appropriate entry in the aircraft log book.

(O) 1. The flight will be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).B. End of procedure.

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ATA 21

33-1 (O) 1. Perform below check of the Cabin Differential Pressure Indicator and CabinAltitude Indicator, with both engines running in Flight Idle.A. Set the L+R BLD VALVE switch to RESET/AUTO (AIR COND panel).B. Set the L+R HP VALVE switch to AUTO (AIR COND panel).C. Set the MODE selector switch to AUTO (Center pedestal).D. Set the landing altitude to 1000 feet below the actual airport elevation

(Center pedestal).

E. Set Barometric set knob to actual airfield pressure + 1.0 in HG (Centerpedestal).

F. Set the CAB PRESS test switch in up position (TEST 2 panel).G. Correct function of the Cabin Differential Pressure Indicator and Cabin

Altitude Indicator are indicated by:– An increase in DIFF PRESS (Max obtainable diff pressure is 0.4 – 0.5 psi).– CABIN ALT to decrease.

H. End of procedure.

2. The flight must be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).

B. End of procedure.

33-2 (O) 1. Perform below check of the Cabin Differential Pressure Indicator with bothengines running in Flight Idle.A. Set the L+R BLD VALVE switch to RESET/AUTO (AIR COND panel).B. Set the L+R HP VALVE switch to AUTO (AIR COND panel).C. Set the MODE selector switch to AUTO (Center pedestal).D. Set the landing altitude to 1000 feet below the actual airport elevation


pedestal).F. Set the CAB PRESS test switch in up position (TEST 2 panel).G. Correct function of the Cabin Differential Pressure Indicator is indicated

by:– An increase in DIFF PRESS (Max obtainable diff pressure is 0.4 – 0.5 psi).

H. End of procedure.

(Continued)

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ATA 21

2. Use below chart to establish Cabin Altitude.

SAAB 340 DIGITAL CPCS AUTO–SCHEDULE AIRCRAFT ALTITUDE DIFF. PRESSURE CABIN ALTITUDE

(feet) (psid) (feet)SEA LEVEL (A/C on ground) 0 -140

SEA LEVEL (A/C in flight) 0.1 -250

2000 0.3 -2504000 1.3 -2506000 2.2 -2508000 3.0 -11510000 4.0 27512000 4.5 73514000 5.1 119516000 5.6 168518000 6.0 220520000 6.5 2725

22000 6.8 342524000 6.9 420026000 7.0 508028000 7.0 605030000 7.0 701531000 7.0 7500

CPS–SYSTEM PRESSURE TOLERANCE +/– 0.10 psidDIFF. PRESSURE TOLERANCE +/– 0.20 psidCABIN ALTITUDE TOLERANCE UP TO 10000 ft +/– 200 ftCABIN ALTITUDE TOLERANCE UP TO 20000 ft +/– 600 ft

3. The flight must be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).B. End of procedure.

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ATA 21

33-3 (O) 1. Perform below check of the Cabin Altitude Indicator with both engines

running in Flight Idle.

A. Set the L+R BLD VALVE switch to RESET/AUTO (AIR COND panel).B. Set the L+R HP VALVE switch to AUTO (AIR COND panel).C. Set the MODE selector switch to AUTO (Center pedestal).D. Set the landing altitude to 1000 feet below the actual airport elevation


pedestal).F. Set the CAB PRESS test switch in up position (TEST 2 panel).G. Correct function of the Cabin Altitude Indicator is indicated by:

– CABIN ALT to decrease.H. End of procedure.

2. Use the Cabin Pressure Auto Schedule chart in item 21–33–2 to establishCabin Differential Pressure.

3. The flight must be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).


33-4 (O) 1. Perform check of the Cabin Differential Pressure Indicator and Cabin

Altitude Indicator in accordance with item 21–33–1 Operational

Procedures.

OR

2. The flight must be conducted in an unpressurized configuration.A. Set the PRESS DUMP switch to ON (EMERGENCY panel).B. End of procedure.

50-1 (M) 1. Extension of the Ram Air Intake.The Ram Air Intake is located on the normal ground Air Connection panel.A. Open the panel and remove the screw on the inside.B. Extend the intake and secure with the same screw from the outside

position.C. Make appropriate entry in the aircraft log book.

(Continued)

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ATA 21

(O) 2. Check that the Avionic Rack Fan operates normally.A. Set the L and R BAT switch to ON (DC ELEC panel).B. Set the right TEMP SELECT switch to neutral position (AIR COND panel).C. Set the ESS AVION switch to ON (DC ELEC panel).

– The fan can easily be heard and not to be mistaken of the sound from theCockpit Temperature Sensor.

D. End of procedure.

3. The Ram Air Intake, which is only extendable on the ground, is located onthe Ground Air Connection Door and must be extended before the flight asa precaution if the remaining Air Conditioning Pack should fail during flight.The ram air ventilation is then provided automatically. The check valve,upstream of the ground connection, is normally kept closed by pressure fromthe working pack but will be opened by ram air pressure after a pack failure.

60-1 (M) 1. Ref. item 21–50–1 Air Conditioning Pack.

(O) 1. Ref. item 21–50–1 Air Conditioning Pack.

60-2 (O) 1. Since the temperature limit circuits are deactivated in manual mode,extreme care must be taken not to obtain a temperature below freezing inthe distribution duct. Therefore always keep the RECIRC FAN ON for thatpack which is operated in manual mode.

2. A temperature below freezing is indicated by ”snow” blowing through thegaspers or frost freezing in the gasper nozzle. This situation can block thesystem creating an overpressure high enough to damage the distributionducting or coves.

(Continued)

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3. For operation in manual mode, hold the TEMP SELECT switch first to HOTposition for 8 sec, to achieve a reference position, dual control valve in hotend position, then set the switch to COLD for 3 sec thereby getting thevalve in mid position. (Normal travelling time between valve max COLDand max HOT is 6 seconds). Allow the system to stabilize for approximately 5min and then if required adjust the temperature by momentarily setting theTEMP SELECT switch to either HOT or COLD POSITION. From aircraft serie nr133 and above monitor CABIN duct TEMP IND to avoid an freezing or

overtemperature situation.

ATA 23

10-2 (O) Flight Crew must continuously monitor appropriate radio frequencies to assureoperational control.

30-1 (O) 1. Operation procedure to ensure appropriate briefings is provided to thepassengers. The pilot will check that the Cabin/Flight Deck InterphoneSystem operates normally and will give appropriate briefing directly to thepassengers. These briefings will include pre-takeoff, pre-landing, after

landing and additional emergency briefings required as deemed necessaryby the flight crew.

30-2 (O) 1. The pilot will check that the PA System operates normally. Prior to flight, thepilot in command must brief cabin crew members on the alternateemergency procedures that will be used.

1.a Prior to flight, the pilot in command should brief cabin crew members onthe alternate procedures to be used. Communication normally conductedusing the flight deck handset can be conducted using the headset/boommicrophone or using the hand microphone and headset or flight deckspeakers.

1.b Use procedures for flight attendant alerting be based on the use ofremaining operative functions of the alerting system or on use of thePassenger Address System. Prior to flight, the pilot in command should briefcabin crew members on the alternate procedures to be used.

50-2 (O) Check normal operation of the headsets and boom microphones.

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50-3 (O) Use flight interphone for communications with ground crew during ground

handling operations (jack is available at the external power receptacle). If

communications still cannot be established, alternate communications procedures

available can be make. Flight Crew must be in accordance with maintenance

personnel for to include hand signals for communication. i.e. "ok to start engine", "gear

pins out", "ok to taxi", "shut down", etc.

50-4 (O) Flight crew must be in accordance with maintenance personnel to support

communication during ground operations across the Ground Intercom System.

ATA 2421-1 (M) NOTE: The following inspection can be performed by a pilot (if properly

instructed), or by a technician.1. Visually inspect the Generator.

A. Open access door 453BR/463BR (left or right forward nacelle cowl door).B. Visually inspect the Generator for no signs of physical distress and/or oil

leakage.C. Close access doors 453BR/463BR (left or right forward nacelle cowl

door).D. Make appropriate entry in the aircraft logbook.

(O) 1. Set the failed AC GEN to OFF/R (ENGINE panel).The failed side AC system will be supplied with power transferred from theopposite operative AC Generator, except for the Engine Anti Ice System.

22-1 (M) NOTE: The following inspection can be performed by a pilot (if properlyinstructed), or by a technician.

1. Visually inspect the Generator.A. Open access door 453BR/463BR (left or right forward nacelle cowl door).

B. Visually inspect the Generator for no signs of physical distress and/or oilleakage.C. Close access doors 453BR/463BR (left or right forward nacelle cowl

door).D. Make appropriate entry in the aircraft logbook.

(O) 1. Set the failed AC GEN to OFF/R (ENGINE panel).The failed side AC system will be supplied with power transferred from theopposite operative AC Generator, except for the Engine Anti Ice System.

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ATA 24

24-1 (O) 1. Flight Crew will make a briefing before takeoff about the cabin workloadwhen only the Standby VOR/ILS operates normally during flight.

2. Avoid icing conditions

34-2 (O) With one or both engines running set the voltage selector to L BAT/R BAT (DC-ELEC Panel) and check for normal readings (27 volt)

34-3 (M) 1. To check the 71° C Automatic Battery Disconnect.A. Disconnect connector 1PAA–P2 from battery 1PAA or 2PAA–P2 frombattery 2PAA–P2.

B. Insert a jumper lead in connector 1PAA–P2:C and 1PAA–P2:D or 2PAA–P2:C and 2PAA–P2:D.

C. Set L BAT/R BAT switch to ON and check that L BAT/R BAT CautionIndication comes on.

D. Set Voltage Selector to L ESS BUS/R ESS BUS (DC ELEC Panel).The reading should be 0 Volt.

E. Make appropriate entry in the aircraft log book.

(O) 1. Monitor the L/R BAT TEMP Indicator during flight. The BAT HOT CautionIndication should come on at +71° C. If the temperature rises to +71° C setthe affected L/R BAT switch to OFF.

36-1 (O) Pilot must be select the affected Battery (BAT) switch(es) “ON” prior takeoff.

37-1 (M) 1. BAT HOT caution indications verification.NOTE: This procedure is applicable for left and right sides.A. Disconnect connector 1PAA–P2 from battery 1PAA.B. Insert a jumper lead in connector 1PAA–P2:C and 1PAA–P2:D.C. Set the associated BAT switch to ON (DC ELEC Panel).

Check that the associated BAT HOT caution indication comes on andthat the CWP ELEC caution indication starts to flash.

D. Make appropriate entry in the aircraft log book.

(Continued)

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ATA 24

(O) 1. To check that the state of battery charge is adequate.A. After both engines have been started and the DC generators are online,

set the DC AMP/VOLT selector (DC–ELEC Panel) to the L generator.B. Set the L BAT switch to OFF and simultaneously note the difference in

generator current shown on the DC AMP/VOLT indicator. If thedifference is less than 50 Amp. (one scale indication) the battery is

adequately charged.C. Set the L BAT switch to ON.D. Set the DC AMP/VOLT selector (DC–ELEC Panel) to the R generator.E. Set the R BAT switch to OFF and simultaneously note the difference in

generator current shown on the DC AMP/VOLT indicator. If thedifference is less than 50 Amp. (one scale indication) the battery isadequately charged.

F. Set the R BAT switch to ON.G. If the difference in generator current was more than 50 Amp. for either

or both of the batteries, wait three minutes while batteries are chargingand then repeat the procedure above.

NOTE: According to the MRB the battery capacity is checked at regularintervals. Therefore the charging check is sufficient to verify thatthe state of battery charge is adequate.

40-1 (O) Flight Crew must verified that the batteries indicators read 28 VDC beforeStarting Engines.

ATA 25

21-1 (M) Flight Attendant Seat(s): Remove or secure the inoperative seat in the stowedposition.

(O) The flight attendant assigned to the affected seat must occupy a passengerseat as close to or closer than the nearest seated passenger to theassociated exit. The flight attendant must be able to reach the assignedemergency exit in essentially the same time as from the normally assignedseat, i.e., a 2 or 3 second time difference is considered "essentially the sametime".

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ALS REV: 2

DATE: 05/15/2011

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ATA 2521-2 (O) 1.Aerolineas Sosa assigns a hand flashlight to each crewmember (3) on duty.

2. The flight attendant will storage the flashlight in the compartment nearestto the seat assigned to her.

(M) Remove or secured the inoperative flashlight holder.

21-3 (M) 1. Remove the affected door(s), ref. AMM 25–28–20.

23-10 (O) Crewmember Interphone System, Flight Deck-to-Cabin, Cabin-To-Flight DeckFunction must be operative.

60-1 (M) Entry in the aircraft records the date of initial removal, the make, model, serialnumber, and reason for removing the transmitter, and a placard located in view of thepilot to show “ELT not installed.”

60-3 (M) 1. SEAT INOPERATIVE SECURED IN UPRIGHT POSITION2. SEAT INOPERATIVE OTHER THAN UPRIGHT POSITION:

a. Secure seat in breakover position with a strap or rope such that seat cannot be moved during flight. OR

b. If seat is stuck in the recline position:1. Verify that emergency exit is not blocked.2. Block off the row of seats aft of inoperative seat and placard the entire

row DO NOT OCCUPY.(O) Prior to all takeoffs and landings, Cabin Crew will verify that baggage is not

stowed under seats with broken restraining bars.

60-7 (M) Secure the inoperative access door/cover in a manner that will prevent wastefrom being deposited in the compartment.(O) Ensure that sufficient galley/lavatory waste receptacles are available toaccommodate all waste that may be generated on the flight.

60-8 (M) 1. Deactivation procedures for most cargo restraint or cargo guiding equipment areeither obvious (e.g. inoperative container stop needs to be released to retracted positionor removed to prevent interference with cargo loading) or unnecessary (e.g., a damagedend stop can be left as is). With the exception of the restrictions below, no otherprocedures are provided.2. Refer to the Weight and Balance Manual for cargo loading limits when operating withrestraint components missing or inoperative. A missing or broken restraint may reduce theallowable size and weight of cargo that requires tie- down restraint.

62-10 & -15. Each inoperative or incomplete EMK and AED must be sealed and clearlylabelled to identify the missing or inoperative components, as appropriate.

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ATA 2611-2 (O) 1. To check the L and R ENG Fire Pull Handle lights and the Fire Bell.

A. Hold the FIRE switch to L (TEST 1 Panel).Check that the L ENG Fire Pull Handle light and the Fire Bell operatenormally.

B. Hold the FIRE switch to R (TEST 1 Panel).Check that the R ENG Fire Pull Handle light and the Fire Bell operatenormally.

C. End of procedure.

13-2 (O) 1. To check that the remaining cargo compartment fire extinguisher systemoperates normally:A. Check that the CARGO EXTG light is not illuminated for the remaining

cargo compartment fire extinguisher system.2. To operate in accordance with appropriate AFM limitations/procedures.

A. Use half the normal 2 bottles fire protection duration times stated in theAFM, i.e. 35 or 30 min. depending on lavatory position (AFM section 2”Limitations”) .

B. Use AFM procedures for operation with a single bottle (section 3

”Emergency Procedures”)

13-3 (M) Remove avionic rack door IAW AMM Ref. 26-13-05

22-2 (M) 1. Empty waste receptacles.2. Lock lavatory door using exterior locking feature.

(O) NOTE: If the associated lavatory smoke detector operates normally, noadditional procedures are required.1. If the associated lavatory smoke detector is inoperative, ensure that the

affected lavatory is kept locked and is not entered except to inspect it.2. Flight attendants should be aware of the location of the nearest portable

fire extinguisher.

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ATA 2712-1 (M) 1. To secure the affected ROLL trim tab in neutral position:

A. Check that the affected ROLL trim tab is neutral position within 1 unit.If not, use the associated actuator push rods to place the affected rolltrim tab into neutral position.It should be emphasized that the possibility to adjust, by means of thepush rods, is limited.

B. Disconnect the associated Trim Actuator Connector, cap and secure the

Connector.C. Placard the inoperative ROLL Trim System.D. Make appropriate entry in the aircraft log book.

13-1 (O) 1. To check that the associated Roll Trim operates normally.A. Use the associated Roll Trim switch in both directions and visually check

that the trim tab moves to the max deflection positions.2. To check a neutral Roll Trim setting.

A. Engage gustlock and visually check a neutral Trim setting. During flightuse primarily the Trim with operating Indicator.

21-1 (M) 1. Deactivation of the Rudder Limiter.A. Electrically power ON.B. Set the RUD LIM switch in OVRD position and wait for approx.10 sec. to

ensure that the electrical actuator has placed the rudder limiter in theoverridden position.

C. On the LH circuit breaker panel pull and secure circuit breaker RUDDERLIMIT (G5).

D. On the RH circuit breaker panel pull and secure circuit breaker RUDDERLIMIT OVRD (N7).

E. Make appropriate entry in the aircraft logbook.

(Continued)

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ATA 27

(O) 1. To check full rudder travel (this procedure require two persons):A. Electrically power ON.B. Place the observer behind the aircraft in full view of rudder and fin.C. Apply full rudder in both directions and check that the center of the

rudder leading edge is approximately aligned with the fin surface whenreaching max rudder deflections. See sketch below.This check confirms that the rudder rudder limiter is not stuck in the 6.5_ or

15_positions.D. End of procedure.

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ATA 27

23-1 (O) 1. To check that the YAW Trim operates normally.A. Use the YAW trim switch in both directions and visually check that the

trim tab moves to the max deflection positions.2. Engage gustlock and visually check for a neutral trim setting.

32-1 (M) 1. Deactivate and secure the system.A. Pull PITCH TRIM SYNC circuit breaker N–6 on the RH circuit breaker panel

10VU.B. Tag and safety the circuit breaker.C. Make appropriate entry in the aircraft logbook.

(O) 1. Manually keep MAIN and STBY PITCH trims synchronized and max trimsplitabove 180 KIAS never to exceed 1 unit. The speed limit 180 KIAS is caused bystructural strength reasons.

33-1 (O) 1. To check that the Left PITCH trim operates normally (requires two persons):A. Operate the main pitch trim by means of the control wheel switch to fully

up and fully down positions.B. Visually check that the trim tab moves accordingly.

C. Synchronize the pitch trims with PITCH RESET (Center pedestal).D. End of Procedure.

2. To check that the Right PITCH trim operates normally (requires two persons):A. Operate the stby pitch trim by means of the STBY PITCH switch (Center

pedestal) to fully up and fully down positions.B. Visually check that the trim tab moves accordingly.C. Synchronize the pitch trims with PITCH RESET (Center pedestal).D. End of Procedure.

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35-3 (O) 1. Perform below stall warning system test prior to each flight.A. Set the STALL 1 and 2 switches simultaneously to upwards (TEST 1 Panel).

STALL 1 and 2 simultaneously upwards initiates left and right stick shakers,aural stall warning, PUSH 1 and PUSH 2 Status Indications and stick push.


53-1 (O) CAUTION: Check the area to be free from obstructions.1. Set the Flaps to all detent positions and visually check that one pointer and

both Flaps travels to the corresponding position.

ATA 28

21-1 (M) Overwing fueling IAW AMM Ref. 12-10-28 (2)(C)

21-2 (M) 1. To deactivate and close the Defuel Valve:A. Open right wing–to–fairing 152AB and Access Panel 151AB (Ref. AMM 53–

50–05).B. Remove Access Panel 601AZ.C. Visually inspect that the Defuel Valve Indicator Pin indicates closed

position and remove and secure the Cannon Plug.D. Make appropriate entry in the aircraft log book.

22-2 (O) Perform either of alternative checks (Alt 1 or Alt 2) of the affected STBY PUMP.1. Alt. 1 – Before engine start.

A. Set the unaffected side STBY PUMP switch to OFF (FUEL Panel).B. Set the unaffected side Condition lever to START (Center Pedestal).C. Check the unaffected side STBY PRESS advisory indication to be out.

If the light is on place the associated condition lever in T/M lock outposition until the light goes out.

D. Set the unaffected side Condition lever to FUEL OFF (Center Pedestal).E. Set the affected side STBY PUMP switch to OVRD (FUEL Panel).F. Set the XFEED switch to ON (FUEL Panel).

Check the unaffected sides STBY PRESS advisory indication to be on. Thatconfirms a correct function of the affected sides standby pump.

G. Return switches to AUTO respective OFF position.H. End of procedure.

(Continued)

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ATA 28

2. Alt. 2 – With both engines running.A. Check the unaffected side STBY PRESS advisory indication to be out.B. Set the affected side STBY PUMP switch to OVRD (FUEL Panel).C. Set the XFEED switch to ON (FUEL Panel).Check the unaffected sides STBY PRESS advisory indication to be on. That

confirms a correct function of the affected sides standby pump.D. Return switches to AUTO respective OFF position.

E. End of procedure.

3. Check L and R MAIN PUMP caution indication to be on prior to engine startand to be out after engine start.

22-3 (M) 1. To close and deactivate the Interconnect Valve:A. Open left wing–to–fairing 151AB and Access Panel 151CB (Ref. AMM 53–

50–05).B. Remove Access Panel 501AZ.C. Visually inspect that the Interconnect Valve Indicator Pin indicates CLSD

position and remove and secure the Cannon Plug.

D. Make appropriate entry in the aircraft log book.

2. Check that both Standby DC pumps operate normally.A. Check the L and R STBY PRESS advisory indication to be out (FUEL panel).

If the light is on place the associated condition lever in T/M lock outposition until the light goes out. Return condition lever to FUEL OFF.

B. Set the L and R STBY PUMP switch to OVRD (FUEL panel).Check that the L and R STBY PRESS advisory indications comes on. Thatconfirms a correct standby pump function.

C. Set the L and R STBY PUMP switch to AUTO (FUEL panel).Check that the L and R STBY PRESS advisory indications goes out.

D. End of procedure.3. Make appropriate entry in the aircraft log book.

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ATA 28

22-4 (M) 1. To close and deactivate the Interconnect Valve:A. Open left wing–to–fairing 151AB and Access Panel 151CB (Ref. AMM 53–

50–05).B. Remove Access Panel 501AZ.C. Visually inspect that the Interconnect Valve Indicator Pin indicates CLSD

position and remove and secure the Cannon Plug.D. Make appropriate entry in the aircraft log book.

2. Check that both Standby DC pumps operate normally.A. Check the L and R STBY PRESS advisory indication to be out (FUEL panel).

If the light is on place the associated condition lever in T/M lock outposition until the light goes out.Return condition lever to FUEL OFF.

B. Set the L and R STBY PUMP switch to OVRD (FUEL panel).Check that the L and R STBY PRESS advisory indications comes on. Thatconfirms a correct standby pump function.

C. Set the L and R STBY PUMP switch to AUTO (FUEL panel).Check that the L and R STBY PRESS advisory indications goes out.


3. Make appropriate entry in the aircraft log book.

22-6 (O) 1. Perform following check to confirm a normal Crossfeed Valve operation.A. Check the L and R STBY PRESS advisory indication to be out (FUEL panel).

If the light is on place the associated condition lever in T/M lock outposition until the light goes out.Return condition lever to FUEL OFF.

B. Set the XFEED switch ON (FUEL panel).C. Set the L or R STBY PUMP switch to OVRD (FUEL panel).

Correct Crossfeed Valve function is confirmed if L and R STBY PRESSAdvisory Indication comes on.

C. End of procedure

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ATA 28

22-7 (O) 1. To check that the affected sides STBY PUMP and STBY PRESS AdvisoryIndication operate normally:A. Check the L and R STBY PRESS Advisory Indication to be out (FUEL panel).

If the light is on place the associated Condition Lever in T/M lock outposition until the light goes out. Return Condition Lever to FUEL OFF.

B. Set the L and/or R STBY PUMP switch to OVRD (FUEL panel).Correct STBY PUMP function is confirmed if L and/or R STBY PRESS Advisory

Indication comes on.C. Return switches to AUTO respective OFF position.D. End of procedure.

41-1 (M) 1. To Check that the LOW LEVEL Caution indication system operates normally.A. Defuel associated fuel tank until the associated LOW LEVEL Caution light

illuminates.B. Verify by Magnetic Dipsticks that the remaining fuel quantity in associated

tank is 300 ± 70 lb / 135 ± 30 kg.(O) 2. Prior to first flight for each crew the crew shall check the fuel quantity.

If the fuel level is less than 1100 lbs/500 kg, check the fuel quantity by

Magnetic Dipsticks before the first flight each day (aircraft level) and for a fuellevel above 1100 lbs/500 kg, use the topoff method and refuel until the overfillswitches close.From the second flight and on each day, the crew may use the upliftmethod to reach required fuel quantity (find the actual fuel level bysubtracting fuel used from the fuel level established before first flight.Order additional fuel as required):

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ATA 28

41-2 (M) Fuel load can be established on Cockpit Fuel Quantity Indicators or if thefuel level is less than 1100 lbs/500 kg by use of Magnetic Dipsticks. Dipstick indexconverting table, ref. item 28–41–1, (aircraft level).

41-3 (M) Normal operation of the cockpit fuel quantity indicator can be verified bycomparing the cockpit fuel quantity indicator reading with the fuel quantityindicated by the Magnetic Dipsticks (if the fuel level is less than 1100 lbs/500 kg).

Dipstick index converting table, ref. item 28–41–1, (aircraft level). For a fuel levelabove 1100 lbs/500 kg, refuel to a known quantity i.e. MID (1640 lbs/745 kg) orFULL level (2950 lbs/1340 kg) and compare with the cockpit fuel quantityindicator reading.

41-4 (M) To verify that the signal between the fuel signal conditioner and the cockpitfuel quantity indicators operate normally, check that the fuel quantity indicatorsmove during the refueling.

41-5 (M) 1. To deactivate the DE–FUEL valve in CLOSE position:A. Set the fuel panel switch to ON.

B. Set the DE–FUEL switch to CLOSE position.C. Set the fuel panel switch to OFF.D. Open right wing–to–fuselage fairing 152AB and Access Panel 151AB(Ref. AMM 53–50–05).E. Remove Access Panel 601AZ.F. Visually inspect that the DE–FUEL Valve Indicator Pin indicates CLSD

position and remove and secure the Cannon Plug.G. Make appropriate entry in the aircraft log book.

(O) 1. On the wing fuel panel check that the fueling control switch for each tankand the FUEL PANEL switch are placed in OFF position.

41-6 (M) CAUTION: Prior to actuating the associated L/R ENG Fire Handle check thatthe Fire Extinguisher switches are in OFF position.

1. Pull the associated L/R ENG Fire Handle (Overhead Panel) and check thatthe position indicator on the Fire Shutoff Valve moves to CLOSED position.

2. Reset the associated L/R ENG Fire Handle (Overhead Panel) and checkthat the position indicator on the Fire Shutoff Valve moves to OPEN position.

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42-1 (M) 1. The associated Cockpit Fuel Quantity Indicator must be verified to operatenormally.

2. The Fuel Quantity Test Function is verified to operate normally. And3. If fuel leakage is detected, verify that the leakage does not exceed

acceptable limits IAW AMM 28-11-00-02 (4).

44-1 (O) 1. Outside Air Temperature (OAT) and Static Air Temperature (SAT) must be

substituted as an indication of fuel temperature.2. IAW AOM chapter FUEL, section LIMITATIONS, the MIN Fuel Operating

Temperature is 40 oC (-40 oF) and, the MAX Fuel Operation Temperatureis +43 oC (+110 oF).

ATA 29

31-2 (O) The mechanical fluid quantity indicator can be seen through a sight windowlocated in the port nose landing gear wheel well (left hand side).

32-1 (O) The accumulator pressure indicators can be seen through a sight windowlocated in the nose landing gear wheel well (right hand side). Starting from thenose going backwards the accumulators are located in the order MAIN, EMER,OUTB BRK and INB BRK.

32-2 (O) The accumulator pressure indicators can be seen through a sight windowlocated in the nose landing gear wheel well (right hand side). Starting from thenose going backwards the accumulators are located in the order MAIN, EMER,OUTB BRK and INB BRK.

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ATA 30

10-1 (M) 1. Verify that the suction hold down is operational by visually checking all De–Ice Boots to be flush with either engine running.

2. Make appropriate entry in the aircraft log book.(O) Flight Crew must check with ATC the forecast by icing condition in route

10-5 (O) 1. Check correct function of the TIMER Caution Indication and the STAB

inflation light. Perform following test with both engines running.A. Set the AIR SUPPLY switch to OFF (ICE PROTECTION panel).B. Set the AUTO CYCLING switch to CONT or ONE CYCLE (ICE PROTECTION

panel).Correct function is indicated by TIMER Caution indication coming on inabout 4 seconds and staying on for approximately 20 seconds.

C. Set the AIR SUPPLY switch to ON (ICE PROTECTION panel).D. Use manual mode STAB push button, press the button for 6 seconds and

observe that the associated STAB inflation light comes on.E. End of procedure.

2. Before dispatch into known or forecast icing conditions check all De–IcerBoots. Use the manual mode push buttons in the following order STAB, WOUTB, W INB, STAB press each button 6 seconds at the time. Observe theassociated Boot Indication Light to come on and visually confirm a normalinflation and deflation.

20-1 (M) Perform Auto Ignition System in associated engine IAW AMM Ref.74-30-00-05-1 Procedure List.

20-3 (O) 1. To check that the associated Engine Anti–Ice System operates normally.A. Operate the affected engine at 92% Ng and set the associated Engine

Anti–Ice System ON.Normal Engine Anti–Ice System operation is confirmed by a decrease inTRQ and an increase in ITT.


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ATA 30

31-1 (O) 1. Check that the Standby Pitot Tube Heater operates normally.A. Set the L and R BAT switch to ON (DC ELEC panel).B. Set the EXT PWR switch to ON (DC ELEC panel).C. Set the STBY PITOT switch to ON (ICE PROTECTION panel).

Normal Standby Pitot Tube Heater function is checked if the STBY PITOTCaution Indication does not illuminate.


31-2 (O) 1. Check that the Main Pitot Tube Heaters operate normally with one ACGenerator on line. Normal Main Pitot Tube Heaters function is confirmed ifthe associated L/R PITOT Caution Indications do not illuminate.

32-1 (O) 1. Check that the Standby Pitot Tube Heater operates normally.A. Set the L and R BAT switch to ON (DC ELEC panel).B. Set the EXT PWR switch to ON (DC ELEC panel).C. Set the STBY PITOT switch to ON (ICE PROTECTION panel).

Normal Standby Pitot Tube Heater function can be checked by

physically sensing that the associated Pitot Tube is hot (withouttouching). The Standby Pitot Tube is the upper one on LH side.

2. Check that the Main Pitot Tube Heaters operate normally with one ACGenerator on line. Normal Main Pitot Tube Heaters function can bechecked by physically sensing that the associated Pitot Tubes is hot(without touching).

3. End of procedure.

41-1 (O) 1. Check that the Right Hand Air Condition Pack operates normally.A. After engine start set the L + R RECIRC switches to ON (AIR COND panel).B. Set the R BLD VALVE switch to RESET/AUTO (AIR COND panel).C. Set the R HP VALVE switch to AUTO (AIR COND panel).

– If hot temperature in the Cockpit:D. Set the F DECK rotary knob to COLD (AIR COND panel).

Check for cold airflow from the Ventilation Outlets.– If cold temperature in the Cockpit:

E. Set the F DECK rotary knob to HOT (AIR COND panel).Check for hot airflow from the Ventilation Outlets.

F. End of procedure.

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42-1 (O) 1. Check that the associated Windshield Heater operates normally.A. Select the associated switch to ON (ICE PROTECTION panel).

Physically check that the associated Windshield is heated (not possible ifOAT above 20° C).

B. End of procedure.ATA 31

50-1 (O) 1. To check the Master Warning Aural Alert (tripple chime) Function.

A. Hold the FIRE test switch to L or R position (TEST1 Panel).Check the Master Warning Aural Alert (tripple chime) function and thefire bell.


50-3 (O) 1. To check the Master Warning Indications.A. Hold the FIRE test switch to L or R position (TEST1 Panel).

saab 340b mel rev2

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