CDL 1 of 18 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.
CDL 2 of 18 The parts not included in this Configuration Deviation List may not be missing. SYSTEM: CHAPTER 23 COMMUNICATIONS NUMBER INSTALLED SE ITEM REMARKS AND /OR EXCEPTIONS Q N 23- Static dischargers (4 on each 14 The following static dischargers may be 01 aileron outer tab, and 2 on each missing or elevator, and 2 on the rudder). damaged: 1 on each aileron outer tab, and 1 on each elevator, and 1 on the rudder. 2 23- Main landing gear static discharge One or both may be missing or damaged. 02 cables.
CDL 3 of 18 NUMBER INSTALLED 1 1 1 1 1 1 REMARKS AND/OR EXCEPTIONS 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 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. SYSTEM: CHAPTER 53 FUSELAGE SE PART DESCRIPTION Q N 53- Access panel to nose landing gear 01 front door release mechanism, 1414 AR. 53- Wash-water servicing panel, 141 02 AB. 53- Toilet servicing panel, 131 AB. 03 Galley water servicing panel, 171 53- AB 04 External power receptacle panel, 53-5 122 AR. 53-06 Air-conditioning ground air supply cover, 312 AR. 1 May be missing. May be missing provided: Flight is performed unpressurized,
CDL 4 of 18 53-07 Tail skid and 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.
CDL 5 of 18 SYSTEM: CHAPTER 53 NUMBER INSTALLED FUSELAGE 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.
CDL 6 of 18 SYSTEM: CHAPTER 54 NUMBER INSTALLED NACELLES SEQ N PART DESCRIPTION REMARKS AND/OR EXCEPTIONS 54- Rear part of tail cone 2 Both may be missing. 01 (Part of 451 AT -461 AT). 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- EN LANDING OFF ROUTE one 35 (77) 30 (66) 25 (55) side 54- Collector tank booster pump and drain 2 both 70 (154) 60 (132) 50 (110) 02 access panels, 432 GR 442 GL. 2 54-03 Tail cone access panels 451 BB 461 BB (if installed). 2 Both may be missing. 54- Accessory bay access panels, 491 AT 492 AT. Both may missing. 04 Both may be missing provided the airspeed is limited to 180 kt IAS.
CDL 7 of 18 SYSTEM: CHAPTER 55 STABILIZERS SEQ PART DESCRIPTION NO. 55- Vertical, and horizontal 01 stabilizer leading edges. Rudder trim and balance tab 55- control 02 fairings, 325 BL -325 EL. Elevator trim tab control fairing, 55-344 FB. 03 Horizontal stabilizer tips, 332 AL 342 AR. 55- Rudder hinge bracket and 04 shroud inspection panels 55-324 AC 324 BC -324 CC. NUMBER INSTALLED REMARKS AND/OR EXCEPTIONS - 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 2 Being several small dents (e.g. hail- stone) distributed along the leading edge(s) of 2 mm in depth are permitted. 1 For the vertical stabilizer leading edge up to 10 % of these dents may have a depth of 4 mm. 2 One or both may be missing provided: a. fairings 326 CL and/or 327 CL are 3 removed, and b. flight is not conducted into known or forecast icing conditions. May be missing provided:
CDL 8 of 18 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
CDL 9 of 18 SYSTEM: CHAPTER 55 NUMBER INSTALLED STABILIZERS SEQ N PART DESCRIPTION REMARKS AND/OR EXCEPTIONS 55- Elevator hinge bracket and shroud 8 One on each side may be missing. 06 inspection panels, 333 AC - 333 BC - 333 CC 333 DC - 343 AC - 343 BC 343 CC 343 DC. Rudder hinge access panels 4 One may be missing. 55-325 CI - 325 DL -325 FL 07 325 GL. Elevator hinge access panels 8 One on each elevator may be missing. 334 AB - 334 BB - 334 CB 55-334 DB - 344 AB - 344 BB 08 344 CB - 344 DB. Rudder tab fairings, 2 One or both may be missing. 326 CL 327 CL. 55- Elevator tab fairing, 345 FB. 1 May be missing. 09 55-10
CDL 10 of 18 NUMBER INSTALLED REMARKS AND/OR EXCEPTIONS - 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. SYSTEM: CHAPTER 57 WINGS SEQ PART DESCRIPTION NO. 57- Wing leading edges 01 57-02 57-03 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 2. Multiple damage Being several small dents (e.g. hailstone) 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.
CDL 11 of 18 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
CDL 12 of 18 SYSTEM: CHAPTER 57 WINGS SEQ PART DESCRIPTION NO. NUMBER INSTALLED REMARKS AND/OR EXCEPTIONS b. flight is not conducted into known or forecast icing conditions. 57- Aileron hinge bracket and 5 One on each side may be missing 04 shroud inspection panels, 532 AC 532 BC - 632 AC - 632 BC 632 FC. 6 One on each side may be missing. 57- Aileron hinge access panels, 05 535 CB - 535 DB - 535 EB 635 CB - 635 DB - 635 EB. 2 One or both may be missing provided flight is Fuel tank vent outlet fairings, not conducted into know or forecast icing 57-534 BB 634 BB. conditions. 06 1 Aerodynamic flap seals. One or more parts may be missing. Loose parts should be removed. 57-07
CDL 13 of 18 SYSTEM: CHAPTER 57 WINGS SEQ ITEM N 57- Pressure re/defueling 08 connection cover, 621 GB. NUMBER INSTALLED REMARKS AND /OR EXCEPTIONS 6 Each fairing may be missing. Aileron hinge access 57-09 panels, 535 HT - 536 GB - 537 JB 635 HT - 636 GB - 637 JB. 22 One panel may be missing provided: The opposite panel is removed, and. Flap extension is limited to 25 degrees. 57- Wingshroud panels, 531 AC Aircraft weight penalty in kg (lb) with shroud panels missing: 10 531 BC - 531 CC - 531 DC 531 FC - 531 GC - 531 AIRCRAFT CONFIGURATION HC. 531 JC - 631 AC 631 BC 631 CC - 631 DC - 631 FC. TAKE- OFF EN ROUTE LANDING 631 GC - 631 HC - 631 JC 931 AC - 931BC 931 35 (77) 30 (66) 25 (55) CC. 932 AC - 932 BC - 932 CC.
CDL 14 of 18 FUSELAGE
CDL 15 of 18 POWER PLANTS AND NACELLES
CDL 16 of 18 HORIZONTAL STABILIZER
CDL 17 of 18 LH WING
CDL 18 of 18 RH WING