EASA AD No : 2010-0217 

EASA Form 110 Page 1/3 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0217 

Date: 21 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) : 

F28 aeroplanes 

TCDS Number : EASA.A.037 

Foreign AD : Not applicable 

Supersedure : None 

ATA 28 Fuel – Fuel Quantity Indication System – Inspection / Modification 

[Fuel Tank Safety] 

Manufacturer(s): Fokker Aircraft B.V. (and predecessor companies) 

Applicability: F28 Mark 1000, 1000C, 2000, 3000, 3000C, 3000R, 3000RC and 4000 

aeroplanes, all serial numbers. 

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

Aviation Administration (FAA) have published Special Federal Aviation 

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

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

Services on the Fokker F28 type design in response to these regulations 

revealed that, on certain aeroplanes, an interrupted shield contact may exist 

or develop between the housing of an in-tank Fuel Quantity Indication (FQI) 

cable plug and the cable shield of the shielded FQI system cables in the main 

and collector fuel tanks which can, under certain conditions, form a spark gap. 

This condition, if not detected and corrected, may create an ignition source in 

the tank vapour space, possibly resulting in a wing fuel tank explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this AD requires, for certain aeroplanes, a 

one-time inspection to check for the presence of a by-pass wire between the 

housing of each in-tank FQI cable plug and the cable shield and, depending 

on findings, the installation of a by-pass wire. In addition, this AD requires the 

implementation of a Critical Design Configuration Control Limitations 

(CDCCL) task to make certain that the by-pass wire remains installed. 

On later production aeroplanes, a different plug has been introduced, Souriau 
EASA AD No : 2010-0217 

EASA Form 110 Page 2/3 

Part Number (P/N) 20P227-2. This plug has an improved shield connection to 

the housing of the plug, for which the installation of a by-pass wire is not 

necessary. For aeroplanes with the improved plug installed, this AD only 

requires the implementation of a CDCCL task to make certain that this type of 

plug remains installed. 

Effective Date: 04 November 2010 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) For F28 serial numbers 11003 through 11041 and 11991 through 

11994: At a scheduled opening of the fuel tanks, but not later than 84 

months after the effective date of this AD, inspect for the presence of a 

by-pass wire between the housing of each in-tank FQI cable plug and the 

cable shield in accordance with Part 1 of the Accomplishment Instructions 

of Fokker Services Service Bulletin (SB) SBF28-28-053 Revision 1 (R1). 

(2) If, during the inspection as required by paragraph (1) of this AD it is found 

that a by-pass wire is not installed, before next flight, install the by-pass 

wire between the housing of the in-tank FQI cable plug and the cable 

shield in accordance with Part 2 of the Accomplishment Instructions of 

Fokker Services SBF28-28-053 R1. 

(3) After determining that by-pass wires are installed, as required by 

paragraph (1) of this AD, or after the installation of by-pass wires, as 

required by paragraph (2) of this AD, as applicable, make certain that a 

by-pass wire remains installed between the housing of each in-tank FQI 

cable plug and the cable shield, in compliance with the requirements of 

this AD. 

(4) Compliance with the requirement of paragraph (3) of this AD can be 

demonstrated by: 

(4.1) Revising as follows the approved aircraft maintenance programme 

for which the Operator or the Owner ensures the continuing 

airworthiness of each operated aeroplane: 

incorporate CDCCL-1 in accordance with the information in 

paragraph 1.L.(1).(c). of Fokker Services SBF28-28-053 R1, 

 and 

(4.2) Complying with the approved aircraft maintenance programme 

described in paragraph (4.1) of this AD. 

(5) For F28 serial numbers 11042 through 11241: From 3 months after the 

effective date of this AD, make certain that Souriau P/N 20P227-2 plugs 

remain installed at all in-tank FQI cable plug positions. 

(6) Compliance with the requirement of paragraph (5) of this AD can be 

demonstrated by: 

(6.1) Revising as follows the approved aircraft maintenance programme 

for which the Operator or the Owner ensures the continuing 

airworthiness of each operated aeroplane: 

incorporate CDCCL-2 in accordance with the information in 

paragraph 1.L.(1).(c). of Fokker Services SBF28-28-053 R1, 

 and 

(6.2) Complying with the approved aircraft maintenance programme 

described in paragraph (6.1) of this AD. 

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

date of this AD, in accordance with Fokker Services SBF28-28-053 

original issue dated 22 June 2010, are acceptable to comply with the 

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

and corrective actions must be accomplished in accordance with Fokker 

Services SBF28-28-053 R1. 
EASA AD No : 2010-0217 

EASA Form 110 Page 3/3 

Ref. Publications: Fokker Services SBF28-28-053 Revision 1 dated 20 September 2010. 

The use of later approved revisions of this document 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 03 September 2010 as PAD 10-092 for 

consultation until 01 October 2010. No comments were received during 

the consultation period. 

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