Attachment_022_SEMA_Appendix_R_PWS

W58RGZ-15R-0045 APPENDIX R TO SEMA PWS

MAINTENANCE DEVIATION LISTS

FOR

SEMA AIRCRAFT

MARSS Beechcraft Model 300

EO-5

MC-12S/W/LPA B-300/B300C (350 & 350ER)

RC-12

Table of Contents

Maintenance Deviation List (MDL) For MARSS Beechcraft Model 300 Aircraft

Maintenance Deviation List (MDL) For EO-5 Aircraft

Maintenance Deviation List (MDL) for MC-12S/W/LPA

B-300/B-300C (350 & 350 ER) Aircraft

Maintenance Deviation List (MDL) for RC-12 Aircraft

SEMA

Maintenance Deviation List (MDL) For MARSS Beechcraft Model 300 Aircraft

Fixed Wing Aviation has developed a Maintenance Deviation List (MDL) to be used in support of this contract. This MDL consists of, but is not limited to, aircraft secondary airframe, engine, propeller, environmental, indicating systems, lights, electrical, avionics and appliances that may be inoperable or not be installed based upon a mission configuration. The aircraft may remain flyable in a specifically configured profile or in compliance with a specific procedure or equipment functionality called for or specified in a U.S. Army approved aircraft Required Equipment List (REL) for that aircraft. The MDL will not include structural or safe flight component. The MDL is a Fixed Wing Aviation document and not an FAA approved document.

This MDL will not be used by the flight crew to determine aircraft mission airworthiness.

All systems and components required by the REL in its entirety for all phases of flight such as, but not limited to, meteorological conditions, airworthiness conditions or mission accomplishment or that place the aircraft in a hazardous condition and render it un-airworthy will not appear on the MDL. If an Item appears on the MDL and the requirements for a complete component and related systems is less than the NUMBER REQUIRED on the REL to meet the requirements for meteorological conditions, airworthiness or mission accomplishment, the item (s) may be deferred per the MDL.

Items that appear on the MDL will be entered into the aircraft logbook as deferred by the MDL. The write up will include the ATA Code and Item Number and state: Item Deferred Per MDL Code and Item with appropriate Aircraft Status Symbol, i.e., Circle X for an item that impedes or restricts the aircraft from the Mission Profile As Described in

AR 700-138.

Items from the MDL are entered in the aircraft logbook and FFIT at the time of discovery (same day as occurrence). The time from entry in the log book to repair completed will comply with the below table.

CONUS OCONUS

POF UND "B" Supply Time 72 120

Repair Time 48 48 Total Time in hours 120 168

At the expiration of the time limit allotted, the aircraft status shall revert to an X condition and the aircraft will be reported NMC for the purpose of the contract. Written request for relief can be submitted to the PCO for approval. This reporting status does not affect the unit DA 1352 reporting status.

If the Government elects to fly the aircraft for any period in the above day calendar period the allotted time for repair shall be extended for a 24 hour period.

Examples:

21 AIR

CONDITIONING

Installed Number Authorized For Deferral

STATUS RESTRICTION

Pressurization Controller

1 1 PMC Restricted to unpressurized flight

MARSS Beechcraft Model 300 ATA Code 21, Installed 1 each Pressurization Controller Required for PRESSURIZED flight 1 each, Pressurization Controller can be deferred, but the aircraft is PMC as it cannot meet its AR 700-138 mission profile.

COMMUNICATION

Installed Number Authorized For

Deferral

STATUS RESTRICTION

1) Communications Systems (VHF, UHF, SATCOM, HF Digital Communications Systems. As installed

As Installed As Installed PMC Aircraft Restricted from Flight into controlled airspace without required communications equipment per AR 95-1 and FAA FAR.

MARSS Beechcraft Model 300 ATA Code 23, Communications (1) Communications Systems (VHF, UHF, SATCOM, HF Digital Communications Systems. As installed. As Installed indicates all VHF, UHF, SATCOM, HF Digital Communications Systems are required for flight into Controlled Airspace.

Items that are noted as 120/168 indicate that the system or systems may be inoperative for 5 Days CONUS or 7 Days OCONUS. The fault shall be entered in the logbook with a black / symbol. After the 120/168 ( hour) period expires the entry shall be upgraded to an X symbol for contract reporting status.

ITEM ATA CODE

NUMBER

INSTALLED NUMBER

AUTHORIZED

FOR

DEFERRAL

STATUS

RESTRICTION

Must be Repaired Within 5 Days CONUS and 7 Days OCONUS

21 AIR CONDITIONING

2. Cabin Altitude (red)

Annunciator System

(ALT WARN)

(CABIN ALT HI)

1 1 PMC May be inoperative provided the aircraft is operated at or below 10,000 feet MSL.

May be inoperative provided the aircraft is configured and operated unpressurized.

3. Cabin Differential High Annunciator System

1 1 PMC May be inoperative provided

4.

1)

Cabin Altitude Warning Horn System

Cancel Switch

1 1 PMC

PMC

May be inoperative provided the aircraft is operated at or below 10,000 feet MSL

May be inoperative provided Cabin Altitude (white) and Cabin Altitude (red) annunciators are both operative.

May be inoperative provided aircraft is configured and operated unpressurized.

May be inoperative provided the aircraft is operated at or below 10,000 feet MSL.

5. Outflow Valve 1 1 PMC May be inoperative provided:

a) Airplane is configured and operated unpressurized, and

b) The Safety Valve is secured open.

6. Safety Valve (Dump) 1 1 PMC May be inoperative provided:

a) Airplane is configured and operated unpressurized, and

b) The Safety Valve is secured open.

7. Differential Pressure / Cabin

Altitude Indicator 1 1 PMC May be inoperative provided aircraft is configured and operated

8. Cabin Rate of Climb Indicator 1 1 120/168

May be inoperative for pressurized flight provided Differential Pressure/Cabin Altitude Indicator is operative.

May be inoperative provided unpressurized.

9. Pressurization Controller 1 1 PMC May be inoperative provided aircraft is configured and operated unpressurized.

10. Vapor Cycle Air Conditioning System

1 1 PMC May be inoperative provided the aircraft Prime Mission Gear is not turned on.

13. L or R BL AIR OFF

2 1 120/168

14. Cabin Door Seal System 1 1 PMC May be inoperative provided

15. Aft Heat System 1 1 120/168 Circuit Breaker must be secured open.

16. Electric Heat System 1 1 120/168 Circuit breaker must be secured open.

17. Cabin Temperature Indicator System

1 1 120/168

18. Environmental Bleed Air Systems (Environmental)

One may be inoperative provided:

a) Environmental Bleed Air

Valve on inoperative side is verified closed prior to each flight,

b) Aircraft is operated at or below Flight Level 250, and

c) Bleed Air Off Annunciator is operative on the operative Environmental Bleed Air System.

May be inoperative provided:

a) Aircraft is configured and operated unpressurized,

b) Both Environmental

Bleed Air Valves are verified closed prior to each flight, and

Cabin temperatures remain suitable for operation.

19.

Environmental Temperature Control System

May be inoperative provided:

a) Aircraft is configured and operated unpressurized,

b) Both Environmental

Bleed Air Valves are verified closed prior to each flight, and

c) Cabin temperatures remain suitable for operation

2)

Automatic Function

Manual Function

120/168

Manual Function is operative.

Automatic Function is operative.

22. Aft Blower 1 1 PMC Aircraft Prime Mission Equipment will not be operated.

22 AUTOFLIGHT

1.

Autopilot System

Autopilot Mode Control Panel Switch Indicator Lamps (Collins FCS Only) If Installed

Autopilot Mode Annunciator Panel Lamps (Collins FCS- 65 Only) If Installed.

a) The Rudder Boost System is verified operative prior to departure in accordance with the Airplane Flight Manual, and

b) Operations do not require use of autopilot the affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS Display or Mode Annunciator Panel.

May be inoperative provided the affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilots EFIS.

2.

Yaw Damper 1 aircraft is operated at or below 5,000 feet MSL

May be inoperative provided:

a) STC SA4733NM (Raisbeck Engineering Dual Aft Body Strakes) is installed and

b) Aircraft is operated at or below 18,500 feet MSL

3. Autopilot Control Wheel

Disengage Switches

(AP/YD/RB/TRIM DISC)

2 1 120/168

One may be inoperative on the non-flying pilot side provided:

a) Autopilot is not used below 1,500 feet AGL, and

b) Approach minimums do not require the use of the autopilot

a) Autopilot is considered inoperative, and

b) Second level switch trim interrupt function remains operative.

a) Autopilot is considered inoperative,

b) Electric Elevator Trim is considered inoperative, and

c) Yaw Damper is considered inoperative

4. Autopilot/Flight Director Go-Around Button

-- -- 120/168 May be inoperative provided:

a) Approach minimums do not require its use, and

b) Alternate procedures are established and used to disconnect the Autopilot and establish initial pitch and wings level attitude.

5.

Flight Director System

Flight Director Mode Control Panel Switch Indicator Lamps (Collins FCS-65 Only) If

Installed.

Flight Director Mode Annunciator Panel Lamps

a) Approach procedures do not require use of Flight Director, and

b) Autopilot is verified

a) Approach procedures do not require use of Flight Director, and

b) Autopilot is considered inoperative affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS Display or Mode Annunciator Panel.

(Collins FCS-65 Only) If Installed.

affected mode(s) is/are selected momentarily prior to departure to verify that proper Mode Annunciation is displayed on the pilot’s EFIS Display

23 COMMUNICATIONS

1. Communications 2 1 120/168 Any in excess of those required by 95-1 or mission requirements may be inoperative provided it is not powered by an Emergency Power Source and not required for Emergency

Procedures.

2. Cockpit Speaker System

(Includes Audio Amp) 2 1 120/168 One may be inoperative provided an operative headset is available to the flight crew.

May be inoperative provided:

a) Two operative Headsets are available to the flight crew, and

b) All aural warnings are available.

5. Static Discharge Wicks 22 -- 120/168 May be damaged or missing provided:

a) No more than two (2) total static wicks are damaged or missing, and

b) Only one (1) static wick is missing from each static discharge general area (left wing, right wing, tail)

6.

3)

Cockpit Voice Recorder (CVR)

For Operators Other Than Air Carriers and Commercial Operators

8.

Boom Microphones (Including headset MICS)

With FDR and Cockpit Voice Recorder Equipped to Record Boom Microphone

With Only Cockpit Voice

9. High Frequency (HF) Communication System

1 1 120/168 May be inoperative unless required by mission profile.

12. Flight Crew Intercom System 5 3 120/168 All positions must be functional for mission or mission training.

13. Flight Phone System (If Installed)

1 1 120/168 May be inoperative unless required by mission profile.

14. Hand Held Microphone 2 1 120/168 Right side may be inoperative provided Second –Command is not required.

18. Selective Call Systems (If installed)

1 1 120/168 May be inoperative unless required by mission profile.

19. Communication Systems UHF/SATCOM ARC-231 (If Installed)

- 1 120/168 Communication Systems must be operational as required for mission profile.

24 ELECTRICAL POWER

1. DC Generator Annunciators 2 1 120/168 One may be inoperative provided both DC Loadmeters are operative and monitored.

3. AC Inverters 2 1 PMC One may be inoperative provided:

a) Aircraft is operated in day VMC only.

4. Cabin AC Power System 1 1 120/168 May be inoperative if not required for mission.

5. Standby Power System 1 1 PMC May be inoperative provided:

a) Airplane is operated day VFR only, and

b) Standby Battery is disconnected and removed

6. External Power System and Annunciator

1 1 120/168

8. L or R GEN BUS TIE Relay 2 1 PMC One may be inoperative provided:

a) Aircraft is operated day

VMC only, and

b) Both DC GEN

Annunciators are

9. L or R GEN BUS TIE

Annunciator 2 1 120/168 May be inoperative provided:

a) Affected Generator Bus Tie Relay is verified CLOSED prior to each departure, and

b) Both DC GEN Annunciators are verified operative prior to each departure.

25 EQUIPMENT

FURNISHINGS

1. Flight Crew Seats armrest(s)

-- -- 120/168 May be inoperative provided the affected Armrest can be placed in the normal up or down position.

11. “FASTEN SEAT BELT” /

“FASTEN SEAT

BELT WHILE SEATED”

Signs or Placards

-- -- 120/168 One or more signs or placards may be illegible or missing provided a legible sign or placard is visible from each occupied passenger seat.

15. Flashlight 1 1 120/168 As required by FAR. Crew must have functional flashlights

17. Crew Assist Straps 2 2 120/168 May be damaged or missing

18. Cockpit Sun Visors 2 0 120/168 May be inoperative or missing provided there is no visual restriction to the flight crew.

24. Mission Crew Seats 3 3 120/168 Must be fully functional for each mission crew member.

26 FIRE PROTECTION

1. Portable Fire Extinguishers 2 1 120/168 Any in excess of those required by AR 95-1 may be inoperative or missing provided:

a) Inoperative Fire Extinguisher is tagged inoperative, removed from its installed location, and placed out of sight so that it cannot be mistaken for a functional Unit, and

b) Required distribution is maintained.

5. Engine Fire Extinguisher PUSH

TO EXTINGUISH Guard 2 2 120/168 May be broken, missing or lacking

Safety Wire provided:

Broken Guard shall not interfere with the proper indication or activation of the Extinguisher

27 FLIGHT CONTROLS

1. Flap Position Indicator 1 1 120/168 May be inoperative provided:

a) Flaps are visually checked for full travel and Flap operation is not restricted, and

b) Flaps are visually checked for proper setting prior to each

3. Trim Tab Indicators (Rudder and Aileron) 2 1 120/168 May be inoperative provided:

a) Tab is visually checked for full range of operation,

b) Tab operation is not restricted, and

c) Tab is positioned to neutral prior to each departure and neural position is verified by visual inspection.

NOTE: Controls must be held neutral to determine Tab Settings.

Electric Elevator Trim System

Trim Switches

PITCH TRIM OFF Annunciator System

Pitch Trim ON-OFF Switch

a) Manual Trim is operative, and inoperative.

Electric Pitch Trim is deactivated,

a) Autopilot is considered inoperative.

28 FUEL

1. Standby Electric Boost Pumps 2 1 120/168 One may be inoperative in accordance with AFM Limitations for operation with Aviation Gasoline and Fuel Crossfeed.

2. Fuel Transfer System Including Annunciator

1 1 120/168 May be inoperative provided Auxiliary Tanks do not contain fuel.

3. Fuel Quantity Annunciators 2 1 120/168 One may be inoperative provided both Fuel Quantity Indicators are operative.

4. Fuel Quantity Indicator System 2 1 120/168 One may be inoperative provided:

a) A reliable means is established to determine that fuel quantity on board meets the regulatory requirements for the flight,

b) Both Fuel Flow Indicators are operative, and

c) Both Fuel Quantity

5. Fuel Crossfeed Annunciator 1 1 120/168 May be inoperative provided:

a) Crossfeed System is verified operative prior to engine start, and

b) Both Fuel Pressure

Annunciator Lights are

8. Engine Driven Low Pressure

Fuel Boost Pumps 2 1 120/168 One may be inoperative provided:

a) Standby Electric Boost Pump is operative and ON, and b ) Aviation Gasoline is not used.

30 ICE AND RAIN

PROTECTION

Engine Inertial Ice Vane Actuator Motors

One Actuator Motor on each inlet may be inoperative provided aircraft is not operated in visible moisture at +5 degrees Celsius (C) or below.

One Actuator Motor on each inlet may be inoperative provided:

a) Inertial Ice Vanes are in the extended position,

b) Appropriate Engine Anti- Ice On Performance Data is used, and

c) Ambient temperature is +10 degrees C or below for takeoff.

Both Actuator Motors of each Inlet may be inoperative provided:

a) Inertial Ice Vanes are in the extended position,

b) Appropriate Engine Anti- Ice On Performance Data is used, and

c) Ambient temperature is +10 degrees C or below for takeoff.

2. Heated Fuel Vents 2 2 PMC May be inoperative provided aircraft is not operated in known or forecast icing conditions.

3.

Pitot Heaters

Pitot Heat Annunciator

a) Aircraft is operated VFR only, and

b) Aircraft is not operated in known or forecast icing conditions.

May be inoperative provided both pitot heaters are verified operative

4. Stall Warning Heat (Lift Transducer and Mounting Plate Heater)

1 1 PMC May be inoperative provided

5. Windshield Wipers 2 2 PMC May be inoperative provided aircraft is not operated in precipitation within five nautical miles of the airport of takeoff or intended landing.

6. Surface Deice System (Wings and Horizontal Stabilizer)

1 1 PMC May be inoperative provided

7. Surface Deice Annunciation

1 1 PMC May be inoperative provided

Propeller Deice System

Automatic Control

Manual Control

Propeller Deice Ammeter aircraft is not operated in known or forecast icing conditions.\

May be inoperative provided the Manual System is operative.

May be inoperative provided the Automatic System is operative.

May be inoperative provided aircraft is not operated in known or forecast icing conditions.

9. Windshield Heat 2 2 PMC May be inoperative provided aircraft is not operated in known or forecast icing conditions.

11. L and R ENG ICE FAIL and L and R ENG ANTI-ICE Engine Inertial Ice Vane Annunciators

One may be inoperative on each side.

Both may be inoperative on one or both sides provided:

Inertial Ice Vanes are secured in the extended position,

a) Appropriate Engine Anti-Ice On Performance data is used, and

c) Ambient surface temperature is +10 degrees C or below for takeoff.

31 INDICATING

RECORDING SYSTEMS

1. Clock With Sweep Second Hand or Electrical Digital Clock.

2 1 120/168 One may be inoperative.

2. Flight Hour Recorder 1 1 120/168 May be inoperative provided an alternate way is established to track aircraft time.

3. Flight Data Recorder 1 1 120/168 May be inoperative provided:

Cockpit Voice Recorder (CVR) operates normally.

5. Master Caution Annunciator 2 1 120/168 One may be inoperative provided:

a) Operative side is on P* side.

6. Master Warning Annunciator

2 1 120/168 One may be inoperative provided:

a) Operative side is on P* side.

7. Engine Trend Condition Monitoring System

1 1 120/168 May be inoperative provided alternate procedures are established and used for engine trend monitoring.

32 LANDING GEAR

1. Landing Gear Down Indicator

Lights (Green)

6 3 120/168 One Lamp in each Indicator may be inoperative provided:

One Lamp in each Indicator is operative and provides sufficient illumination for positive Down and Locked Indication

2. Landing Gear Control In-Transit Lights (Red)

2 1 120/168 One Bulb may be inoperative provided all Landing Gear Down Indicator Lights are operative.

3. Hydraulic Fluid Low

1 1 120/168 May be inoperative provided hydraulic fluid level is verified full each flight day.

4. Parking Brake 1 1 120/168 May be inoperative provided procedures are established to ensure a crewmember remains at the brakes until the wheels are chocked or the aircraft is otherwise secured.

5. Brake Deice System 1 1 120/168 May be inoperative provided The crew avoids prolonged taxi operations in snow or slush.

6. Landing Gear Control Down Lock Solenoid

1 1 120/168 May be inoperative provided:

a) Down Lock Latch is verified operative, and

b) Down Lock Release

Button is verified operative.

33 LIGHTS

1. Cabin Lights 120/168 May be partially inoperative provided:

a) Cabin Emergency Exit

Lighting is operative,

b) Sufficient Lighting is available for crew to perform required duties,

c) Sufficient Lighting is operative for passenger carrying operations at night, and

d) Both Cabin Exit Lights are operative.

2. Cockpit/Flight Deck/Flight

Compartment and Instrument Lighting System

120/168 Individual Lights may be inoperative provided remaining Lights are:

a) Sufficient to clearly illuminate all required instruments, controls, and other devices for which it is provided,

b) Positioned so that direct rays are shielded from flight crewmembers eyes, and

c) Lighting configuration and intensity is acceptable to the flight crew.

3. Strobe Lights System 1 1 120/168 May be inoperative if a Beacon

Light System is operative

4. Taxi Light 1 1 120/168 May be inoperative for day operations.

May be inoperative for night if both landing lights are operational

5. Landing Lights 2 1 120/168 May be inoperative for Day operations.

One may be inoperative for night operations provided the taxi light is operative.

7. Position Lights 1 1 PMC May be inoperative provided the aircraft is not operated at night.

8. Anti-Collision Beacon Light System

3 1 120/168 May be inoperative provided a Strobe Light System is operative.

9. Recognition Lights 2 2 120/168

10. Wing Ice Inspection Lights 2 2 120/168 May be inoperative provided a portable lamp/light of adequate capacity for wing and control surface is available for night operations in icing conditions.

11. Passenger Notice System (Fasten Seat Belt No Smoking)

1 1 120/168 May be inoperative provided appropriate verbal briefings are given to the passengers.

12. Baggage Compartment Lights 1 1 120/168

14. Boarding Lighting System (Includes Lights Within the Airstair and in the Entryway Foyer)

-- -- 120/168 May be inoperative provided both Cabin Exit Lights are operative.

15. Emergency Instrument Light System.

1 1 PMC May be inoperative for Day VMC.

34 NAVIGATION SYSTEM only

1. Gyroscopic Rate of

Turn/Slip Skid Indicators

2 1 PMC May be inoperative on right side provided aircraft is operated Day VMC only.

2. Vertical Speed Indicators

2 1 PMC May be inoperative on right side provided the aircraft is operated Day VMC.

3. Weather Radar/Thunderstorm Detection Equipment

1 1 PMC May be inoperative provided flight will not be conducted in an area of known or forecast thunderstorm conditions.

a)

Navigation Equipment

VOR/ILS Systems

TACAN Systems

Glide Slope

Area Navigation (GPS)

Navigation Databases

a) Not required by AR 95-

1/FAR, host country regulations and

b) Operations do not require its use.

operations do not require its use.

May be inoperative provided operations do not require its use.

May be inoperative provided operations do not require its use.

Any in excess of those required by AR 95-1/ FAR/host country regulations or operations may be inoperative.

May be out of currency provided:

a) Current aeronautical charts are used to verify navigation fixes prior to each departure and,

b) Procedures are established and used to verify status and suitability of navigation facilities used to define route of flight.

c) Approach navigation radios are manually tuned and identified, and

d) RNAV departures, RNAV arrivals, instrument approaches and published RNAV routes based on RNAV guidance are not used

5. ATC Transponders and 2 1 120/168 May be inoperative provided:

Automatic Altitude Reporting Systems

a) IAW AR 95-1 one must be operational for IMC flight

b) For VFR any in excess of those required by FAR may be inoperative

6. Marker Beacon System -- -- 120/168 May be inoperative provided approach procedure does not require its use.

8. Radar Altimeter 1 1 120/168 May be inoperative provided:

a) Class A TAWS and/or

GPWS are considered inoperative,

b) TCAS II is considered inoperative,

c) Approach procedures do not require its use, and

d) Alternate procedures are established and used. M) May be inoperative provided TCAS, TAWS and/or GPWS are not affected

10. Distance Measuring Equipment

(DME) Systems -- -- 120/168 May be inoperative provided a suitable operative RNAV system is available for DME substitution.

May be inoperative provided operations do not require its use.

11. Non-Stabilized Magnetic Compass

May be inoperative provided any combination of three Gyro, AHARS, or INS (IRU) Stablized Compass Systems are operative.

May be inoperative provided:

a) Any combination of two

GYRO AHARS or INS (IRU) Stablized Compass Systems operate normally, and

b) Airplane is operated with Dual Independent Navigation Capability And under Positive Radar Control by ATC on the enroute portion of the flight.

May be inoperative for flights that are entirely with the areas of magnetic unreliability provided at least two Stabilized Directional Compass Systems are installed, operate normally, and used in conjunction with approved Free Gyro Navigation Techniques.

13. Automatic Direction Finder

(ADF)

1 1 120/168 May be inoperative provided operations do not require its use.

14. Radio Magnetic Indicator (RMI) -- -- 120/168 May be inoperative provided:

a) Magnetic Compass is operative,

b) Any navigation source not displayed on another indicator is considered inoperative

16. Traffic Alert and Collision Avoidance System (TCAS I)

1 1 120/168 May be inoperative provided:

a) Maybe inoperative on the right side.

17.

Traffic Alert and Collision Avoidance System (TCAS II)

Combined Traffic Alert (TA) and Resolution Advisory (RA) Dual Display System

Traffic Alert (TA) Display System(s)

Resolution Advisory (RA) Display System(s)

a) Not required by

FAR/host country regulations

b) System is deactivated and secured, and

c) Enroute or approach procedures do not require its use.

May be inoperative on the non-flying pilot side provided:

a) TA and RA visual display is operative on the flying pilot side, and

b) TA and RA audio function is operative on the flying pilot side.

May be inoperative provided:

a) RA visual display and audio functions are verified operative, and

b) Enroute or approach procedures do not require its use.

May be inoperative on non-flying pilot side.

May be inoperative provided:

a) Traffic Alert (TA) visual display and audio functions are verified operative,

b) TA ONLY Mode is selected by the crew and

4)

Audio Functions

c) Enroute or approach procedures do not require its use.

enroute or approach procedures do not require use of TCAS.

A.

b) c) d)

Terrain Awareness and Warning System (TAWS)

Class A TAWS Equipment Required by FAR

Ground Proximity Warning System (GPWS)

Modes 1-4

Test Mode

Glideslope Deviation(s) (Mode 5)

Advisory Callouts

Alternate procedures are established and used.

May be inoperative provided:

a) Alternate procedures are established and used.

a) GPWS is considered inoperative.

May be inoperative provided:

a) Operations do not require its use.

May be inoperative provided alternate procedures are established and used.

21. Electronic Flight Instrument System (EFIS) Multi-Function Display Unit (MFD)

1) 3 Tube System

2) 5 Tube System

Multi-Function Processing Unit (MPU) is operative.

May be inoperative provided the Multi-Function Processing Unit (MPU) is operative.

23. Altitude Alerting System - - 120/168 May be inoperative provided:

a) Autopilot with

Altitude Hold is operative,

b) Enroute operations do not require its use

24. Ground Proximity

Altitude Advisory System (GPAAS)

1 1 120/168

27. Flight Management System (Aircraft Integrated Systems)

2 1 120/168 NOTE: Navigation functions and systems identified as FMS that provide only navigation functions are deferred with Area Navigation.

May be inoperative provided:

a) Operations do not require its use, and

b) Affected systems are identified and considered inoperative.

30. Altimeters (Pneumatic/Mechanic al Altimeters Only) (Except Collins

Proline 21 equipped aircraft)

2 1 120/168 May be inoperative on right side provided:

a) Second In Command is not required, and

b) Aircraft is not equipped with Air Data

c) Display Unit(s) or Servoed Electric

Altimeter(s).

31. Airspeed Indicator

(Mechanical Airspeed Indicators Only) (Except Collins Proline 21 equipped aircraft)

2 1 120/168 May be inoperative on right side provided:

Aircraft is not equipped with Air Data Display Unit(s) or Servoed Electric Airspeed Indicator(s).

32. Gyroscopic Directional Indicator Systems (Mechanical Heading Indicators Only)

2 1 120/168 May be inoperative on right side provided:

a) Second in command is not required, and

b) Aircraft is not equipped with EFIS.

33. Gyroscopic Pitch and Bank Indicator Systems (Mechanical Attitude Indicators Only)

May be inoperative on right side provided:

a) Second in command is not required, and

Aircraft is not equipped with EFIS or Servoed Electric Gyroscopic Pitch and Bank Indicator.

ADD. APX-119 1 1 PMC Must be operational for mission operations as required by Commander.

35 OXYGEN

1. Passenger Oxygen System 1 1 PMC Must be operational for Operator training and missions.

2. External Oxygen Gauge 1 1 120/168 May be inoperative provided the Internal Oxygen Gauge is monitored during servicing to avoid over-servicing.

3. Passenger Oxygen Mask -- -- PMC Must be functional at all stations for operator training and missions.

37 VACCUM/PRESSURE

1. Suction Gauge 1 1 PMC May be inoperative provided

46 INFORMATION

SYSTEMS

Integrated Flight Information System (Pro Line 21 IFIS-5000)

File Server Unit (FSU) (FSU INOP Message)

Cursor Control Panel (CCP) alternate procedures are established and used to ensure all information pertinent to the flight is accessible at the pilot station in current and appropriate form.

NOTE: If alternate source is electronic, dual redundancy is required for operation.

May be inoperative provided alternate procedures are established and used to ensure all information pertinent to the flight is accessible at the pilot station in current and appropriate form.

NOTE: If alternate source is electronic, dual redundancy is required for operation.

2. XM Satellite Weather System 1 1 120/168

52 Doors

2. CABIN DOOR Annunciator

System.

1 1 120/168 May be inoperative provided a crewmember confirms, by visual inspection, that all monitored doors are closed and latched prior to each departure.

3. Cabin Door Lock and Upper Door Latch Observation Light System

1 1 120/168 May be inoperative provided a crewmember confirms, by visual inspection, using a flashlight that latches are in the locked position prior to each departure.

4. Cabin Door Snubber 1 1 120/168 Air stair door must be carefully opened.

Air Stair Door Cable Covers

1 1 120/168 May be damaged or missing provided it does not interfere with normal operation of the Cabin Door.

61 PROPELLER

1. Propeller Synchrophaser/Synchronizer System

1 1 120/168

2. Propeller Synchroscope 1 1 120/168

73 ENGINE & CONTROL

1. Fuel Flow Indicators 2 1 120/168 One may be inoperative provided both Fuel Quantity Indicating Systems are operative.

74 IGNITION

2. L or R IGNITION ON

Annunciator 2 1 120/168 One may be inoperative in the illuminated condition.

92 AIRCRAFT

SURVIVABILITY

EQUIPMENT

1. AN/AAR-57 Common Missile Warning System.

1 1 PMC As required by mission.

2. Flare Dispensing Systems 1 1 PMC As required by mission

Maintenance Deviation List (MDL) For EO-5 Aircraft airframe, engine, propeller, environmental, indicating systems, lights, electrical, avionics and appliances that may be inoperable or not be installed based upon a mission configuration. The aircraft may remain flyable in a specifically configured profile or in compliance with a specific procedure or equipment functionality called for or specified in a U.S. Army approved aircraft Required Equipment List (REL) for that aircraft. MDL will not include structural or safe flight component. The MDL is a Fixed Wing Aviation document and not an FAA approved document.

This MDL will not be used by the flight crew to determine aircraft mission airworthiness.

All systems and components required by the REL in its entirety for all phases of flight such as, but not limited to, meteorological conditions, airworthiness conditions or mission accomplishment or that place the aircraft in a hazardous condition and render it un-airworthy will not appear on the MDL. If an Item appears on the MDL and the requirements for a complete component and related systems is less than the NUMBER REQUIRED on the REL to meet the requirements for meteorological conditions, airworthiness or mission accomplishment, the item (s) may be deferred per the MDL.

Items that appear on the MDL will be entered into the aircraft logbook as deferred by the MDL. The write up will include the ATA Code and Item Number and state: Item Deferred Per MDL Code and Item with appropriate Aircraft Status Symbol, i.e., Circle X for an item that impedes or restricts the aircraft from the Mission Profile As Described in

AR 700-138.

Items from the MDL are entered in the aircraft logbook and FFIT at the time of discovery comply with the below table

Time 72 120

At the expiration of the time limit allotted the aircraft status shall revert to an X condition and the aircraft will be carried, for the purposes of the contract, as NMC. Written request for relief can be submitted to the PCO for approval. This reporting does not affect the unit DA 1352 reporting status.

CONDITIONING

Installed Number That Can Be deferred

STATUS RESTRICTION

Pressurization Controller

1 1 PMC Restricted to unpressurized flight

EO-5 ATA Code 21, Installed 1 each Pressurization Controller Required for PRESSURIZED flight 1 each, Pressurization Controller can be deferred, but the aircraft is PMC as it cannot meet its AR 700-138 mission profile.

23 COMMUNICATION INSTALLED Number That Can

Be Deferred

STATUS RESTRICTION

1) Communications Systems (VHF, UHF, SATCOM, HF Digital

As Installed As Installed PMC Aircraft Restricted from Flight into controlled airspace without required communications equipment per AR 95-1 and

FAA FAR.

EO-5 ATA Code 23, Communications (1) Communications Systems (VHF, UHF, SATCOM, HF Digital Communications Systems. As installed. As Installed indicates all VHF, UHF, SATCOM, HF Digital Communications Systems are required for flight into Controlled Airspace.

Items that are noted as 120/168 indicate that the system or systems may be inoperative for 5 Days CONUS or 7 Days OCONUS. The fault shall be entered in the logbook with a black / symbol. After the 120/168 (120/168 hour) period expires the entry shall be upgraded to a X symbol for contract reporting status.

ATA CODE

AND ITEM

NUMBER

INSTALLED NUMBER

AUTHORIZED

FOR

Must be Repaired Within 5 Days CONUS and 7 Days

OCONUS

1 Air Conditioning Packs

1) With Mod 7/1493

Installed

One may be inoperative provided Emergency Ram Air Recovery System operates normally.

2 Nacelle Flow Control Valves 4 2 120/168 One may be inoperative on each side provided:

a) Both air conditioning packs operate normally, and

b) Inoperative valves are deactivated.

3 BLEED AIR Caution Light 1 1 120/168 May be inoperative provided Engine Bleed switches are verified OFF during takeoff and landing.

4 Cabin Pressure Control

1) Automatic

2) Manual

3) Automatic and Manual manual control operates normally.

May be inoperative provided automatic control operates normally.

May be inoperative provided flight is conducted in an unpressurized configuration.

5 Rear Outflow Valves 2 1 PMC May be inoperative provided flight is conducted in an unpressurized configuration.

6 Differential Pressure Indicator

1 1 PMC May be inoperative:

a) Cabin Altitude Indicator operates normally, and

b) A chart is provided to convert cabin altitude to differential pressure. OR

c) Flight is conducted in an unpressurized configuration.

7 Cabin Altitude Indicator 1 1 PMC May be inoperative:

a) Cabin Altitude Indicator operates normally, and

b) A chart is provided to convert cabin altitude to differential pressure. OR

c) Flight is conducted in an unpressurized configuration.

8 Cabin Rate of Climb

Indicator 1 1 PMC May be inoperative provided:

a) All other instruments and functions of the pressurized operate normally. OR

b) Flight is conducted in an unpressurized configuration.

9 CABIN PRESS Caution Light

1 1 PMC May be inoperative provided:

a) Flight remains at 10,000 ft MSL or below. OR

b) Supplemental oxygen is used as required by the crew IAW AR 95-1 and Federal Aviation Regulations are met.

22 AUTO PILOT

1 1) Autopilot System

1) Individual Modes

Inoperative operations do not require its use.

Individual modes may be inoperative provide procedures do not require its use.

2 Yaw Damper 1 1 120/168 May be inoperative.

3 Control Wheel

Autopilot/Yaw Damper Disengage Switches

One control wheel disengage switch may be inoperative provided:

a) Autopilot is not used below 1,500 AGL, and

b) Center Glare Shield Panel guarded Yaw Damper switch is off, and

c) Approach minimums do not require its use.

May be inoperative provided the Autopilot is not used.

4 Autopilot Disengaged Caution Light

1 1 120/168 May be inoperative provided the Autopilot is not used.

23 COMMUNICATION

1 Flight Compartment Speakers 2 2 120/168 May be inoperative provided:

a) Procedures do not require their use, and

b) Headsets are installed and operate normally.

2 Flight Compartment Hand Microphones

2 2 120/168 May be inoperative provided:

a) Procedures do not require their use, and

b) Headsets are installed and operate normally.

3 Crew Intercommunication System including Audio Control Panels and Associated Headsets

-- 2 120/168 Any in excess of the flight deck crewmembers may be inoperative.

OR

For every flight, the number of operational Audio Control Panels and Headsets must equal the number of personnel (performing flight/mission related duties), occupying the mission are in addition to the numbered required for the flight deck.

4 Intercommunications Systems Cabin PA Speakers

-- --- 120/168 May be inoperative provided crewmembers in mission area have functional headsets connected to the Aircraft Intercommunications system.

5 Flight Deck to Ground Interphone System

1 1 120/168 May be inoperative provided:

a) Procedures do not require its use, OR

b) Pre-coordinated visual signaling is used.

6 Communication Systems

(HF,VHF,UHF,SATCOM,

Radio Transceivers and Controls)

-- 2 120/168 Any in excess of one fully functional VHF-22C and one additional, cockpit accessible radio system, capable of VHF ATC Communications, may be inoperative provided they are not required to meet planned flight or mission requirements.

7 LRCS (HF,SATCOM) 2 PMC May be inoperative provided:

a) They are not required to meet planned flight or mission requirements, and

b) They are not required for operation of aircraft over water for more than 30 minutes of 100NM from Land.

8 Static Dischargers 16 4 120/168 A maximum of four may be missing provided not more than one is missing from each sitting or control surface group.

9 Cockpit Voice Recorder System (CVR)

1 1 120/168 May be inoperative provided:

a) Flight Data Recorder (FDR) operates normally.

10 Boom Microphone (on CVR Control Head)

1 1 120/168 May be inoperative provided:

a) Flight Data Recorder operates normally, and

b) Cockpit Voice Recorder is considered inoperative.

11 Emergency Locator Transmitter

1 1 PMC An operational ELT is required for all mission flights.

24 ELECTRICAL

1 AC Generator System

(Generator & Related GCU 4 2 PMC Two may be inoperative provided:

a) Cause of malfunction is determined, and

b) Appropriate action is taken that no hazard exists, and

c) Airplane is not flown into known or forecast icing conditions, and

d) Dispatching does not require fuel transfer.

2 AC GEN Caution Lights 4 2 PMC Two may be inoperative provided:

a) All generators are verified to operate normally throughout flight, and

b) Airplane is not operated in known or forecast icing conditions, and

c) Dispatching does not require fuel transfer.

3 AC GEN HOT Caution lights 4 2 PMC Two may be inoperative provided:

a) Associated generators are removed and secured by an acceptable procedure, and

b) Aircraft is not flown into known or forecast icing conditions, and

c) Dispatching does not require fuel transfer.

25 EQUIPMENT AND

1 Cabin Area Seats (other than Mission Analysts and Jump Seats

1) Seat Backs

May be occupied with inoperative seat back recline adjustment provided seatback is secured in upright position.

May be inoperative in other that the upright position provided:

a) It does not block and Emergency Exit.

b) Does not restrict any passenger from access to the main aircraft aisle.

c) The associated seat(s) is blocked and placarded “DO

NOT OCCUPY.”

d) An inoperative seat belt is considered inoperative.

2 “Fasten Seat Belts While Seated” signs or Placards

-- -- 120/168 One or more signs or placards may be inoperative, illegible, or missing provided a legible sign or placard is readable for each occupied passenger seat.

3 Pilots and Mission Analysis Seat Adjustment

1) Vertical Mode

Vertical mode adjustment may be inoperative provided:

a) Seat is secured and meets the individual Crewmember’s requirements, and

b) Fore and Aft adjustment operates normally.

4 Flight Attendant Seat Assembly (single or Dual Position)

-- -- 120/168 May be inoperative provided the associated seat is placarded “DO NOT

OCCUPY.”

5 Forward Observer Seat (Including Associated Equipment)

1) Forward Observers Audio Selector Panel

May be inoperative.

Forward observers audio selector panel may be inoperative provided:

a) Occupant of the seat is not required to perform official duties, and

b) An occupant may, after being briefed on the nature of the discrepancy elect to utilize the seat, and

c) The pilot not flying will aurally brief the occupant of all briefings normally heard and understood by the flight crew.

6 Cabin Emergency Flashlight Holders/Flashlights

-- -- 120/168 May be inoperative or missing provided the crew member assigned to the associated position has a normally operating flashlight readily available.

7 First Aid Kit -- 0 120/168 Individual First Aid Kits may be inoperative provided:

a) 1 Kit is accessible and available to the crew and,

b) 1 Kit is available for each 7 persons onboard the aircraft.

8 Overhead Storage Bin Latches

-- -- 120/168 May be inoperative provided:

a) Affected storage bin lids(s) is secured closed,

b) Affected bin is not used for storage of any items except for those permanently affixed, and

c) Any emergency equipment located in the affected compartment is considered inoperative, and

d) Affected bin is placarded

“INOPERATIVE DO NOT

USE.”

9 Toilet 1 1 120/168 May be inoperative provided:

a) Flight duration does not require its use, and

b) Door to lavatory entrance is clearly marked

INOPERATIVE DO NOT

USE, and

c) There is no chemical leakage.

10 Crew Mission Position Jump Seats

2 2 120/168 May be inoperative provided:

a) affected seat(s) are secured in stowed position and,

b) Placarded “DO NOT

OCCUPY.”

11 Non-Essential Equipment and Furnishings

-- -- 120/168 Non-Essential Equipment and Furnishing items, as expressed in this MCDL, are those not related to crewmember convenience, comfort or entertainment such as, but not limited to, galley equipment, overhead reading maps, etc.

26 FIRE PROTECTION

1 Engine Fire Detection

Systems 8 4 120/168 Either Loop A or Loop B may be inoperative on each engine.

2 Baggage Compartment Smoke Detectors

One may be inoperative with no special procedures.

May be inoperative provide:

a) Inner baggage door, if installed, remains open, and

b) Compartment contents are properly restrained. OR

c) Only non-combustible materials are carried.

3 Fire Extinguisher Thermal and Discharge Discs

4 4 120/168 May be missing provided indicator readings are checked once each flight day to verify adequate charge.

4 Fire Bell Warning 1 1 120/168 May be inoperative provided all Fire Warning Lights operate normally.

5 Cargo Compartment Smoke Detectors

3 3 120/168 May be inoperative provided cabin area is monitored by a crewmember.

6 Lavatory Fire Extinguisher 1 1 120/168 May be inoperative provided Lavatory is used only by crewmembers.

7 Lavatory Smoke Detection Systems

1 1 120/168 May be inoperative provided Lavatory is used only by crewmembers.

8 APU Fire Detection Systems

1 120/168 Either Loop A or Loop B may be inoperative provided the other loop is verified as operational.

9 APU Fire Extinguishing System

1 1 120/168 May be inoperative provided the APU is considered inoperative and not used.

27 FLIGHT CONTROLS

1 Aileron Trim Indicator 1 1 120/168 May be inoperative provided:

a) Aileron Trim is verified to have full and free movement.

2 Stall Warning Systems 2 1 120/168 One may be inoperative provided the associated system is deactivated.

3 Rudder Trim Indicator 1 1 120/168 May be inoperative provided:

a) Rudder Trim is verified to have free movement and,

b) Rudder Trim is verified neutral before each departure.

4 Trailing Flap System 1 1 120/168 May be inoperative provided:

a) System is secured, and

b) Operations are conducted in compliance with the AFM.

5 Flap Positions Indicators 1 1 120/168 May be inoperative provided:

a) Flap position markings are legible on the inboard nacelles, and

b) Flaps operate normally through 25 degrees travel, and

c) Proper flap position is visually verified by a qualified person other than a flight deck crew member, and

d) Flaps are limited to 25 degrees.

6 Spoilers Advisory Lights

1) ROLL INBD

2) ROLL OUTBD

3) GROUND

al PFCS SPOILERS indicators operate normally, and are monitored closely.

May be inoperative provided all PFCS SPOILERS indicators operate normally and are closely monitored.

May be inoperative provided:

a) System is deactivated, and

b) Appropriate performance decrements are applied.

7 Ground Spoiler System 1 1 120/168 May be inoperative in the DOWN position provided:

a) System is deactivated, and

b) Appropriate performance decrements are applied.

8 Powered Flight Control System (PFCS) Indicators

1) RUDDER (RUD)

2) SPOILERS (LO,LI,RI,

RO)

Maybe inoperative provided a visual flight control check is accomplished before each flight.

May be inoperative provided:

a) ROL INBD and ROLL OUTBD spoilers advisory lights operate normally, and

b) A visual flight control check is accomplished before each flight.

9 Rudder Hydraulic Pressure Caution Lights (#1 RUD

2 1 120/168 One maybe inoperative provided the RUD 1 and

HYD, #2 RUD HYD) RUD 2 actuators are verified to operate normally before each departure.

10 Rudder Pedal Adjustment 2 2 120/168 May be inoperative provided rudder pedals can be secured in a position which meets individual pilot requirements.

11 Gust Lock System 1 1 120/168 May be inoperative provided:

a) The Gust Lock System tension spring moves and holds the Gust Lock Control Lever to the unlocked/off position (full forward), and

b) Elevator/Aileron controls have a full range of motion for normal operation with no binding.

12 Trailing Flap Actuator Locking System

1 1 120/168 May be inoperative.

13 Rudder Trim Switch

1) Return to Center Spring

May be inoperative

a) Rudder Trim Indicator operates normally, and

b) Rudder Trim Switch is manually returned to center detent position after each selection of the Rudder Trim.

28 FUEL

1 AC Auxiliary Fuel Pumps 4 1 120/168 One may be inoperative provided:

a) Flight compartment fuel quantity indicators operate normally, and

b) Airplane is dispatched so that fuel transfer is not required.

2 Fuel Quantity Indicators

1) Main Tanks

2) Auxiliary Fuel Tanks

a) Fuel quantity in associated tank is verified using the Magnastick, or is verified visually.

b) All four Fuel Flow Meters operate normally

c) Flow is monitored during flight, and

d) Fuel Consumption is recorded.

Quantity Indicator a) Fuel quantity in associated tank is verified using the Magnastick, or is verified visually, and

b) All four Fuel Flow Meters operate normally

c) Flow is monitored during flight, and

d) Fuel Consumption is recorded.

3 Fuel Tank Indication System (Refueling Panel)

4 4 120/168 May be inoperative provided fuel quantity is verified through the use of Magnasticks or the fuel quantity is verified visually at each refueling.

4 Pressure Refueling System 1 1 120/168 May be inoperative 5 TANK FUEL LOW caution lights provided associated fuel quantity indicator operates normally and is monitored during flight.

May be inoperative provided

a) Associated fuel quantity indicator (s) operates normally, and

b) Airplane is dispatched so as to assure flight completion with a minimum of 700 lb fuel in related tanks (s) and,

c) Dispatching does not require fuel transfer.

6 FUEL XFR System Caution Light

1 1 120/168 May be inoperative provided dispatching does not require fuel transfer.

7 FUELING ON Caution Light 1 1 120/168 May be inoperative provided Refuel/Defuel POWER ON light operates normally and is verified extinguished after each refueling.

8 ENG FUEL PRESS Caution Lights

4 1 120/168 One may be inoperative provided:

a) Associated Fuel Flow Meter operates normally, and

b) Associated auxiliary pump operates normally, is selected ON before departure, and remains ON throughout the flight.

9 Aux Pump Advisory Lights 4 4 120/168 May be inoperative

a) Associated auxiliary pump(s) and ENG FUEL PRESS caution light(s) operates normally, and

b) Dispatching does not require fuel transfer.

10 Fuel Tank Magnasticks,

1) Main Fuel Tank

2) Auxiliary Fuel Tank

a) A placard is place on the Fuel Transfer panel which states Magnasticks inoperative, and

b) Following each refueling, fuel quantity is verified at flight compartment and/or Refuel/Defuel panel.

May be inoperative provided:

a) A placard is placed on the Fuel Transfer panel which states Magnasticks inoperative, and

b) Following each refueling, fuel quantity is verified at flight compartment and/or Refuel/Defuel point, OR

a) The auxiliary fuel system is not used, and

b) No fuel enters the tanks during refueling.

29 Hydraulic Power 1 System Quantity Indicators 2 1 120/168 May be inoperative provided:

a) Quantity is verified adequate before each departure, and

b) Associated ENG HYD PUP caution lights and pressure indicator operates normally.

2 System Pressure Indicators 2 2 120/168 May be inoperative provided associated ENG HYD PUMP caution lights, and

a) quantity indicator(s) operate normally.

3 ENG HYD PUMP caution lights

4 2 120/168 One may be inoperative for each hydraulic system provided the associated pressure indicator and associated pump are verified to operate normally before each departure.

30 ICE/RAIN

PROTECTION

1 Airframe De-Icing System (Wing, Tail and Engine Intake)

1 1 PMC May be inoperative provided the aircraft is not operated in known or forecast icing conditions

2 Elevator Anti-Icing System 1 1 PMC May be inoperative provided aircraft is not operated in known of forecast icing condition.

3 Engine Intake Deflectors

May be inoperative retracted provided airplane is operating into know or forecast icing conditions, or in visible precipitation with temperatures +5 degrees C.

May be inoperative deployed provided operations comply with AFM.

4 Engine Intake Deflector Indicators

4 4 PMC May be inoperative provided aircraft is not operated in know or forecast icing conditions.

5 Propeller De-Icing Systems 4 4 PMC May be inoperative…