EASA AD No: 20 1 2

- 00 23

EASA Form 11 0 Page 1 / 3 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 20 1 2 - 00 23

Date: 0 6 Februar y 201 2

Note: This Airworthiness Directive ( AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may o perate an aircraft to which an AD applies, except in accordance with the requirements of that AD , unless otherwise specified by the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4 ) exemption]. 

### Type Approval Holder’s Name : Fokker Services B.V. Type/Model designation(s) : F28 a eroplanes
TCDS Number : EASA.A.037 Foreign AD : Not applicable Supersedure: None



### ATA 5 2 Doors
– Main Landing Gear Doors
– Inspection / Modification

Manufacturer(s): Fokker Aircraft B.V. Applicability: F28 Mark 0070 and Mark 0 100 aeroplanes , all serial numbers

. Reason: In 2005, s everal occurrences were reported where the bracket of the rod in the Carbon Fibre Reinforced Plastic (CFRP) MLG outboard door had detached , preventing the MLG to lock properly when selected down

. Prompted by these reports, CAA

- NL issued AD NL

- 2006

- 001 (EASA approval 2006

- 0 002) to require the inspect ion and modif ication of the attachment of the operating rod bracket as detailed in Fokker Service Bulletin (SB) SBF100

- 52

- 080

. After that AD was issued, several operators reported broken recessed head s of titanium attachment bolts of the operating rod bracket o n modified (i.e. post

SBF100

- 52

- 080) CFRP MLG outboard door s

. I n such a situation , t he remaining bolt shafts can get pulled through the external repair patch and the carbon fib r e door outer skin , causing the operating rod, with the detached bracket, to get stuck between the MLG main fitting and wing lower skin. The primary factor to the cause of breaking bolt heads has been determined to be incorrect adjustment of the MLG outboard door. This condition, if not detected and corrected, w ould prevent the affected MLG from moving to the down and locked position , poss ibly result in g in MLG collapse during landing or roll

- out and consequent damage to the aeroplane and/or injury to the occupants. To address this potential unsafe condition, Fokker Services has published SBF100

- 52

- 090, providing modification instructions t o install an improvedEASA AD No: 20 1 2

- 00 23

EASA Form 11 0 Page 2 / 3 attachment of the MLG outboard door operating rod. For the reasons described above, this new AD requires a one - time detailed inspection for play or cracks in the recessed bolt heads and, depending on findings, applicable corrective action s , modification of the operating rod bracket attachment to the CFRP MLG outboard door , and introduction of a weaker ( aluminium ) bolt in the attachment of the MLG outboard door operating rod

. Effective Date: 2 0 February 2012 Required Action(s) and Compliance Time(s): Required as indicated, unless accomplished previously. (1) Within 9 months after the effective date of this AD, inspect the CFRP MLG outboard door for play or cracks in the recessed countersunk heads of the operating rod bracket attachment bolts in accordance with Part 1 of the Accomplishment Instructions of Fokker Services SBF100

- 52

- 090 , or accomplish the modification as required by paragraph (3) of this AD

. (2) If, during the inspection as required by parag raph (1) of this AD, play or cracks are found in the countersunk bolt heads, and if CDL item 52

- 07 cannot be applied , before next flight, accomplish one of the actions specified in paragraph B of part 1 of the accomplishment instructions of Fokker Services SBF100

- 52

- 090. (3) Within 24 months after the effective date o f this AD, or prior to installation of a CFRP MLG outboard door (see Note below) , whichever occurs later, modify the CFRP MLG o utboard d oors and a ttachment to the MLG in accordance with Part 2 of the Accomplishment Instructions of Fokker Services SBF100

- 52

- 090. Note: As the aluminium MLG outboard doors and the CFRP MLG outboard doors are two

- way interchangeable, the modification of paragraph (3) applies only to aeroplanes that currently have al uminium doors installed when such a door is (to be) replaced with a CFRP door. (4) From the effective date of this AD, do not install on an aeroplane any MLG outboard door having Part Number (P/N) D13310

- 401 through

- 418 or any MLG outboard door assembly having P/N D13312

- 401 through

- 410

. CAA

- NL AD NL

- 2006

- 001 (EASA approval 2006

- 002) contains the requirement to modify all spare MLG outboard door assemblies having P/N D13312

- 401 through

- 410, t o P/N D13312

- 7XX standard, in accordance with the instructions of Fokker Component Service Bulletin (CSB) D13312

- 52

- 09. (5) From the effective date of this AD, do not install on any aeroplane a P/N D13310

- 701 through

- 7 0 8 MLG outboard door or a P/N D13312

- 702 through

- 711 MLG outboard door assembly , unless the component has been inspected and modified in accordance with the instructions of Fokker CSB D13312

- 52

- 015.
Ref. Publications: Fokker Services SBF100

- 52

- 090 dated 17 November 2011. Fokker CSB D13312

- 52

- 09 dated 12 December 2005. Fokker CSB D13312

- 52

- 015 dated 17 November 2011. The use of later approved revisions of these document s is acceptable for compliance with the requirements of this AD.
Remarks : 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. This AD was posted on 0 5 January 201 2 as PAD 1 2

- 00 1 for consultation until 02 F ebr uary 2012

. No comments were received during the consultation period

. 3. Enquiries regarding this AD should be referred to the Safety InformationEASA AD No: 20 1 2

- 00 23

EASA Form 11 0 Page 3 / 3 Section, Executive Directorate, EASA; E

- mail ADs@easa.europa.eu

. 4. For any question concerning the technical content of the requirements in th is AD, please contact Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp , The Netherlands; telephone +31

- 88

- 6280

- 350; facsimile + 31

- 88

- 6280

- 1 11; e - mail: technicalservices@fokker.com

. The referenced publication can be downloaded from www.myfokkerfleet.com

.