MINIMUM EQUIPMENT LIST Doc. Ref : MNL-FL-011 Revision...

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MINIMUM EQUIPMENT LIST

APPENDIX CDL CONFIGURATION DEVIATION

LIST F-27 Mk 050

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Minimum Equipment List F-27 Mk 050 Copyright © 2013 Edition 0

GENERAL LIMITATIONS

This Configuration Deviation List contains additional certificate limitations for operation of the

Fokker F27 MK050, MK0502 and MK0604 Airplane without certain secondary airframe and

engine cowl parts or deficiencies concerning airfoil

Leading edges as listed herein.The certificate limitations in the Airplane Flight M annual are

applicable except as amended herein. Differences in airplane versions will be identified with

“(if installed”.

The associated limitations must be listed on a placard affixed in the flight deck on the pilot’s

instrument panel in a clear view of both pilots.

The pilot in command will be notified each operation with (a) missing part(s) by listing the

missing part(s) in the flight or Dispatch release.

The airplane logbook must show appropriate notation covering the missing part(s) or

deficiencies on each flight.

If an additional part is lost in flight, the airplane may not depart the airport at which it landed

following this event until it again Complies with the limitations of this appendix. This, of

course, does not preclude the issuance of a special permit to allow the Airplane to be flown

to a point where necessary repairs or replacements can be made.

No more than one part of any one system in this appendix may be missing unless specifically

designated combinations are indicated herein. Unless otherwise specified herein, parts from

different systems may be missing. The performance penalties are cumulative.

When no performance penalties are listed, no more than a total of three such parts may be

missing before take-off.

Take –off performance penalties are applicable to take-off to gross weights which are

limited by field length, first segment

climb, second segment climb, final segment climb or take-off flight path. En route

performance penalties are applicable to

operations which are limited by en route, flight path performance requirements. Landing

performance penalties are

applicable to landing gross weight which are limited by landing field length, landing climb

or approach climb.

The numbering and designation of systems in this appendix is based on ATA spec. 100.

The parts within each system are

identified by Functional description and, when necessary, by panel numbers.



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The parts not included in this Configuration Deviation List may not be missing.

SYSTEM: CHAPTER 23

COMMUNICATIONS

NUMBER INSTALLED

SE

Q

N°

ITEM

REMARKS AND /OR EXCEPTIONS

23-

01

23-

02

Static dischargers (4 on each

aileron outer tab, and 2 on each

elevator, and 2 on the rudder).

Main landing gear static discharge

cables.

14

2

The following static dischargers may be

missing or

damaged:

1 on each aileron outer tab, and

1 on each elevator, and

1 on the rudder.

One or both may be missing or damaged.



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SYSTEM: CHAPTER 53

FUSELAGE

NUMBER INSTALLED

SE

Q

N°

PART DESCRIPTION REMARKS AND/OR EXCEPTIONS

53-

01

53-

02

53-

03

53-

04

53-5

53-

06

Access panel to nose landing gear

front door

release mechanism, 1414 AR.

Wash-water servicing panel, 141

AB.

Toilet servicing panel, 131 AB.

Galley water servicing panel, 171

AB

External power receptacle panel,

122 AR.

Air-conditioning ground air supply

cover,

312 AR.

1

1

1

1

1

1

1

May be missing provided: a. It is determined by visual inspection

that the nose landing gear front

door

release mechanism is in the flight

operational position, and

a. b. The cavity is blanked off with high speed tape with a minimum of 50

mm

(2”) overlap all around the

opening

and furnished with a vent hole of

3 mm (0.125”).

NOTE: The tape is not allowed to

become damaged,

frayed or partly detached

because this will

result in negative influence on

the pitot system.

May be missing.

May be missing.

May be missing.

May be missing.

May be missing provided: a. Flight is performed unpressurized,



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53-

07

Tail skid

and

b. The cavity is blanked off with high speed tape with a minimum of 50

mm (2”) overlap all around the opening

and furnished with a vent hole of 3 mm

(0.125”).

May be missing.



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SYSTEM: CHAPTER 53

FUSELAGE

NUMBER INSTALLED

SEQ

N°

PART DESCRIPTION

REMARKS AND/OR EXCEPTIONS

53-

08

Nose Radom (111 AT)

Lightning strips.

8

A strip may be cracked/fractured

provided: a. The length of the

crack/fracture may be not more than 50 per cent

of the

width of the strip.

b. Not more than one crack/fracture per strip,

c. Not more than two strips may be affected,

d. Flight in thunder clouds with active lightning is avoided.

Per strip 3 diamond

segments per foot

strip length may be missing,

provided

not more than 3 missing

diamond segments

are adjacent.



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SYSTEM: CHAPTER 54

NACELLES

NUMBER INSTALLED

SEQ

N°

PART DESCRIPTION


54-

01

54-

02

54-

03

54-

04

Rear part of tail cone

(Part of 451 AT -461 AT).

Collector tank booster pump

and drain

access panels, 432 GR – 442

GL.

Tail cone access panels

451 BB – 461 BB (if installed).

Accessory bay access panels,

491 AT – 492 AT.

2

2

2

2

Both may be missing.

In case an APU is installed in the RH

tail

cone (461 AT ) and the rear part is

missing

operation of the APU is prohibited.

Aircraft weight penalty in kg (lb) with

rear

part on one or both sides missing:

AIRCRAFT CONFIGURATION

TAKE-

OFF

EN

ROUTE

LANDING

one

side

35 (77) 30 (66) 25 (55)

both 70

(154)

60 (132) 50 (110)

Both may be missing.

Both may missing.

Both may be missing provided the air-

speed is limited to 180 kt IAS.



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SYSTEM: CHAPTER 55

STABILIZERS

NUMBER INSTALLED

SEQ

NO.

PART DESCRIPTION


55-

01

55-

02

55-

03

55-

04

55-

Vertical, and horizontal

stabilizer leading edges.

Rudder trim and balance tab

control

fairings, 325 BL -325 EL.

Elevator trim tab control fairing,

344 FB.

Horizontal stabilizer tips,

332 AL – 342 AR.

Rudder hinge bracket and

shroud

inspection panels

324 AC – 324 BC -324 CC.

-

2

1

2

3

Dents in the leading edges may be present

provided the depth is less than 0,5 mm and a

length/depth ratio of at least 20.

1. Big isolated dents

Horizontal stabilizer leading edge:

One dent up to a maximum of 30 mm x 30

mm x 3 mm

(length, width,depth) on each side is

permitted.

Vertical stabilizer leading edge:

Two dents up to a maximum of 50 mm x

50 mm x 4 mm

(length, width,depth) and at least one

meter apart are

permitted.

2. Multiple damage

Being several small dents (e.g. hail- stone)

distributed

along the leading edge(s) of 2 mm in depth

are permitted.

For the vertical stabilizer leading edge up

to 10 % of these

dents may have a depth of 4 mm.

One or both may be missing provided:

a. fairings 326 CL and/or 327 CL are

removed, and

b. flight is not conducted into known or

forecast icing

conditions.

May be missing provided:



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05 a. fairing 345 FB is removed, and


forecast icing

conditions.

One or both may be missing.

One may be missing



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SYSTEM: CHAPTER 55

STABILIZERS

NUMBER INSTALLED

SEQ

N°

PART DESCRIPTION


55-

06

55-

07

55-

08

55-

09

55-

10

Elevator hinge bracket and shroud

inspection panels,

333 AC - 333 BC - 333 CC

333 DC - 343 AC - 343 BC

343 CC – 343 DC.

Rudder hinge access panels

325 CI - 325 DL -325 FL

325 GL.

Elevator hinge access panels

334 AB - 334 BB - 334 CB

334 DB - 344 AB - 344 BB

344 CB - 344 DB.

Rudder tab fairings,

326 CL – 327 CL.

Elevator tab fairing, 345 FB.

8

4

8

2

1

One on each side may be missing.

One may be missing.

One on each elevator may be missing.

One or both may be missing.

May be missing.



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SYSTEM: CHAPTER 57

WINGS

NUMBER INSTALLED

SEQ

NO.


57-

01

57-

02

57-

03

Wing leading edges

Outer flap hinge fairings,

522 CB - 522 DB - 622 CB

622 DB.

Aileron spring and trim tab

control fairings

532 CT - 535 BB - 535 FB

632 CT - 635 BB - 635 FB.

-

4

6

Dents in the leading edges may be present

provided the depth is less than 0,5 mm and a

length/depth ratio of at least 20.

1. Big isolated dents

One dent up to a maximum of 50 mm x

50 mm x 4 mm

(length, width,depth) for each inner wing

is

Permitted. Two dents up to a maximum

of 75 mm x

75 mm x 5 mm (length, width,depth) for

each outer

wing is permitted provided no more

than one dent per

leading edge section.

2. Multiple damage

Being several small dents (e.g. hail-

stone) distributed

along the leading edge(s) of 2 mm in

depth are

permitted Up to 10 % of these dents

may have a

depth of 4 mm.

One or both parts of each fairing may be

missing provided flight is not conducted

into known or forecast icing conditions.



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Each fairing may be missing provided:

a. fairing 535 HT and/or 536 GB

and/or 537 JB and/or 635 HT

and/or 636 GB and/or 637 JB

are removed, and



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SYSTEM: CHAPTER 57

WINGS

NUMBER INSTALLED

SEQ

NO.


57-

04

57-

05

57-

06

57-

07

Aileron hinge bracket and

shroud

inspection panels, 532 AC

532 BC - 632 AC - 632 BC

632 FC.

Aileron hinge access panels,

535 CB - 535 DB - 535 EB

635 CB - 635 DB - 635 EB.

Fuel tank vent outlet fairings,

534 BB – 634 BB.

Aerodynamic flap seals.

5

6

2

1


forecast icing conditions.

One on each side may be missing

One on each side may be missing.

One or both may be missing provided flight is

not conducted into know or forecast icing

conditions.

One or more parts may be missing.

Loose parts should be removed.



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SYSTEM: CHAPTER 57

WINGS

NUMBER INSTALLED

SEQ

N°

ITEM REMARKS AND /OR EXCEPTIONS

57-

08

57-

09

57-

10

Pressure re/defueling

connection cover, 621 GB.

Aileron hinge access

panels,

535 HT - 536 GB - 537 JB

635 HT - 636 GB - 637 JB.

Wingshroud panels, 531

AC

531 BC - 531 CC - 531 DC

531 FC - 531 GC - 531

HC.

531 JC - 631 AC – 631 BC

631 CC - 631 DC - 631

FC.

631 GC - 631 HC - 631 JC

931 AC - 931BC – 931

CC.

932 AC - 932 BC - 932

CC.

6

22

Each fairing may be missing.

One panel may be missing provided: a. The opposite panel is removed, and. b. Flap extension is limited to 25 degrees.

Aircraft weight penalty in kg (lb) with

shroud panels missing:

AIRCRAFT CONFIGURATION

TAKE-

OFF

EN

ROUTE

LANDING

35 (77)

30 (66)

25 (55)



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CAA-01 APPENDIX


FUSELAGE



LIST F-27 Mk 050

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POWER PLANTS AND NACELLES



LIST F-27 Mk 050

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HORIZONTAL STABILIZER



LIST F-27 Mk 050

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CAA-01 APPENDIX


LH WING



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CAA-01 APPENDIX


RH WING

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