Airworthiness Directive · Amendment 39-15851 · Landing gear
Fokker Model F.27 Mark 050 Airplanes
This AD applies to all Fokker Model F.27 Mark 050 airplanes, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F.27 Mark 050 airplanes. This AD requires measuring the length of the extended portion of the sliding member of the main landing gear, performing an inspection for the presence of lockwiring, and doing corrective actions if necessary. This AD results from a report that the sliding member of the main landing gear has been overextended after landing. We are issuing this AD to detect and correct improper installation of the lockwire on the two lockbolts that hold the sliding member end stop, which could result in structural damage of the main gear and loss of control of the airplane during the landing roll, due to main landing gear overextension.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within 500 flight cycles after the effective date of this AD, measure the length of the extended portion of the sliding member of the main landing gear in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF50-32-039, dated July 2, 2007. Repeat the measurement at intervals not to exceed 500 flight cycles until the requirements of paragraph (g) have been completed.
(h) At the applicable time in paragraph (h)(1) or (h)(2) of this AD, perform an inspection for the presence and correct installation of lockwiring on the two end stop lock bolts of the main landing gear, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF50-32-039, dated July 2, 2007. If lockwiring is not present or is not installed correctly, install lockwiring before further flight in accordance with Fokker Service Bulletin SBF50-32-039, dated July 2, 2007.
(1) During any measurement required by paragraph (g) of this AD, if overextension is found, or the measurement has increased by 1.0 millimeter (mm) or more compared to the previous measurement, inspect before further flight.
(2) If no overextension is found and the measurement has not increased by 1.0 mm or more between measurements during the measurements required by paragraph (g) of this AD, inspect within 4,000 flight hours after the effective date of this AD.
Note 1: Fokker Service Bulletin SBF50-32-039, dated July 2, 2007, refers to Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007, as an additional source of service information for measuring the length of the extended portion of the sliding member of the main landing gear, performing an inspection for the presence of lockwiring on the lock bolts of the two end stops, and installing new lockwiring.
(i) If, during any measurement required by paragraph (g) of this AD, overextension is found or the measurement has increased by 1.0 mm or more compared to the previous measurement; or if, during any inspection required by paragraph (h) of the AD, lockwiring is not present or is not installed correctly; submit a report to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; facsimile (31) 252-627-211; e-mail technicalservices.fokkerservices@stork.com, at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include any finding of overextension or incorrect lockwiring to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; facsimile (31) 252-627-211. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056.
(1) If the inspection or measurement was done on or after the effective date of this AD: Submit the report within 30 days after the inspection or measurement, as applicable.
(2) If the inspection or measurement was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
(j) As of 5 months after the effective date of this AD: No person may install a main landing gear on any airplane unless Part B of Messier-Dowty Service Bulletin F50-32-62, dated January 17, 2007, has been accomplished for that part.
