EASA AD No : 2010-0197 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0197 

Date: 01 October 2010 

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 operate 

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) : 

F27 Mark 050, 0502 and 0604 aeroplanes 

TCDS Number : EASA.A.036 

Foreign AD : Not applicable 

Supersedure : This AD supersedes EASA AD 2010-0182 dated 30 August 2010. 

ATA 28 Fuel – Fuel Pipes in Engine Nacelles – Inspection / Replacement 

[Fuel Tank Safety] 

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: F27 Mark 050, 0502 and 0604, serial numbers 20133 through 20335, except 

those with inboard fuel tanks installed. 

Reason: Prompted by an accident of a Boeing 747-131 (flight TWA800), the Federal 

Aviation Administration (FAA) has published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) has 

published Interim Policy INT/POL/25/12. The review conducted by Fokker 

Services on the Fokker 50 and Fokker 60 type design, in response to these 

regulations, revealed that the clearance between parts of the main landing 

gear (MLG) and the fuel pipes may be insufficient. 

This condition, if not detected and corrected, could lead to chafing, possibly 

resulting in fuel leakage and, in combination with other factors, a fuel fire. 

EASA issued AD 2010-0182 to require actions to ensure that a minimum 

clearance is maintained between the parts of the MLG and the fuel pipes in 

both nacelles. 

Since that AD was issued, it was discovered that aeroplane serial numbers 

20133 through 20142 were erroneously omitted in the original Fokker 

Service Bulletins (SB) and consequently the AD did not apply to those 

aeroplanes. The two SB’s (some typographical errors in part numbers were 

also found) have now been revised to correct this omission. 

For the reasons described above, this new AD retains the requirements of 

AD 2010-0182, which is superseded, and expands the Applicability to add 

the 10 missing serial numbers. 
EASA AD No : 2010-0197 

EASA Form 110 Page 2/3 

Effective Date: 15 October 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) Within 6 months after 13 September 2010 [the effective date of AD 

2010-0182], accomplish the following actions concurrently: 

(1.1) Check the part numbers (P/N) of each fuel pipe (two in each 

nacelle) in accordance with Part 1 of the Accomplishment 

Instructions of Fokker Services SBF50-28-028 Revision 1 (R1). 

(1.2) If, as a result of the check as required by paragraph (1.1) of this 

AD, other fuel pipe P/N than specified in Part 1 of the 

Accomplishment Instructions of Fokker Services SBF50-28-028 R1 

are found to be installed, inspect the clearance between the fuel 

pipes and the parts of the MLG, in accordance with Part 2 of the 

Accomplishment Instructions of Fokker Services SBF50-28-028 

R1. 

(2) If, during the inspection as required by paragraph (1.2) of this AD, the 

measured clearance is 3.0 mm or less for one or more fuel pipes, or 

chafing marks are found on one or more fuel pipes, install new fuel 

pipes in both engine nacelles at the time indicated in Table 1 of this AD, 

as applicable, in accordance with the Accomplishment Instructions of 

Fokker Services SBF50-28-031 R1. 

Table 1 – Fuel Pipes Replacement 

Findings: Compliance Time: 

clearance of less than 1.5 mm, 

or chafing marks 

before next flight 

clearance between 1.5 mm 

and 3.0 mm 

within 24 months after 13 

September 2010 [the effective 

date of AD 2010-0182] 

(3) If, during the inspection as required by paragraph (1.2) of this AD, the 

measured clearance of all fuel pipes is 1.5 mm or more, within 4 800 

flight hours (FH) after the inspection as required in paragraph (1.2) of 

this AD, and thereafter at intervals not to exceed 4 800 FH, inspect the 

clearance in accordance with the instructions for the Fuel Airworthiness 

Limitations Item (ALI) in paragraph 1.L.(1).(c) of Fokker Services 

SBF50-28-028 R1. 

(4) If, during any inspection as required by paragraph (3) of this AD, the 

measured clearance is 3.0 mm or less for one or more fuel pipes, or 

chafing marks are found on one or more fuel pipes, install new fuel 

pipes in both engine nacelles at the time indicated in Table 2 of this AD, 

as applicable, in accordance with the Accomplishment Instructions of 

Fokker Services SBF50-28-031 R1. 

Table 2 – Fuel Pipes Replacement 

Findings: Compliance Time: 

clearance of less than 1.5 mm, 

or chafing marks 

before next flight 

clearance between 1.5 mm 

and 3.0 mm 

within 24 months after the 

inspection finding 

(5) Installation of new fuel pipes, optionally or as required by paragraph (2) 
EASA AD No : 2010-0197 

EASA Form 110 Page 3/3 

or paragraph (4) of this AD, as applicable, in accordance with the 

Accomplishment Instructions of Fokker Services SBF50-28-031 R1, 

constitutes terminating action for the repetitive inspections required by 

paragraph (3) of this AD. 

(6) For aeroplanes that are equipped with one or more fuel pipes with 

other P/N than specified in Part 1 of the accomplishment 

instructions of SBF50-28-028: From 13 September 2010 [the effective 

date of AD 2010-0182], each time when fuel pipes are removed and 

refitted or replaced (same P/N), or when a MLG upper member, outer 

cylinder, drag stay or lock link is removed from, or (re)installed in the LH 

or RH nacelle, ensure that the clearance is at least 3.0 mm. 

(7) For aeroplanes equipped with only fuel pipes with P/N as specified 

in Part 1 of the accomplishment instructions of SBF50-28-028: 

From 13 September 2010 [the effective date of AD 2010-0182], or after 

modification of the aeroplane in accordance with the Accomplishment 

Instructions of Fokker Services SBF50-28-031 R1, as applicable, ensure 

that the aeroplane remains in post-SBF50-28-031 R1 configuration. 

(8) Compliance with the requirements of paragraphs (3), (4), (6) and (7) of 

this AD can be demonstrated by: 

(8.1) Revising as follows the approved aircraft maintenance 

programme for which the Operator or the Owner ensures the 

continuing airworthiness of each operated aeroplane: 

 Incorporate the Fuel ALI and Critical Design Configuration 

Control Limitation (CDCCL), as applicable to the aeroplane 

configuration, in accordance with the information in paragraph 

1.L.(1).(c) of Fokker Services SBF50-28-028 R1. 

(8.2) Complying with the approved aircraft maintenance programme 

described in paragraph (8.1) of this AD. 

(9) Inspections and corrective actions accomplished prior to the effective 

date of this AD, in accordance with Fokker Services SBF50-28-028 and 

SBF50-28-031, both at original issue, are acceptable to comply with the 

initial requirements of this AD. After the effective date of this AD, 

inspections and corrective actions must be accomplished in accordance 

with Fokker Services SBF50-28-028 and SBF50-28-031, both at R1. 

Ref. Publications: Fokker Services SBF50-28-028 R1 dated 15 September 2010. 

Fokker Services SBF50-28-031 R1 dated 15 September 2010. 

The use of later approved revisions of these documents 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. The required actions and the risk allowance have granted the issuance 

of a Final AD with Request for Comments, postponing the public 

consultation process after publication.. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any question concerning the technical aspects of the requirements in 

this AD, please contact: 

Fokker Services B.V., Technical Services Dept., P.O.Box 231, 

2150 AE Nieuw-Vennep, The Netherlands; 

telephone (31) 252-627-350; facsimile (31) 252-627-211; 

e-mail: technicalservices.fokkerservices@fokker.com

The referenced publication can be downloaded from 

www.myfokkerfleet.com