MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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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LIST F-27 Mk 050
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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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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.
MINIMUM EQUIPMENT LIST
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LIST F-27 Mk 050
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SYSTEM: CHAPTER 54
NACELLES
NUMBER INSTALLED
SEQ
N°
PART DESCRIPTION
REMARKS AND/OR EXCEPTIONS
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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APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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SYSTEM: CHAPTER 55
STABILIZERS
NUMBER INSTALLED
SEQ
NO.
PART DESCRIPTION
REMARKS AND/OR EXCEPTIONS
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:
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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05 a. fairing 345 FB is removed, and
b. flight is not conducted into known or
forecast icing
conditions.
One or both may be missing.
One may be missing
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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SYSTEM: CHAPTER 55
STABILIZERS
NUMBER INSTALLED
SEQ
N°
PART DESCRIPTION
REMARKS AND/OR EXCEPTIONS
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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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SYSTEM: CHAPTER 57
WINGS
NUMBER INSTALLED
SEQ
NO.
PART DESCRIPTION REMARKS AND/OR EXCEPTIONS
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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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SYSTEM: CHAPTER 57
WINGS
NUMBER INSTALLED
SEQ
NO.
PART DESCRIPTION REMARKS AND/OR EXCEPTIONS
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
b. flight is not conducted into known or
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.
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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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)
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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FUSELAGE
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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POWER PLANTS AND NACELLES
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LIST F-27 Mk 050
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HORIZONTAL STABILIZER
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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LH WING
MINIMUM EQUIPMENT LIST
APPENDIX CDL CONFIGURATION DEVIATION
LIST F-27 Mk 050
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RH WING