Airworthiness Directive · Amendment 39-11876 · Fokker Model F.28 Mark 0100 Series Airplanes
Fokker Model F.28 Mark 0100 Series Airplanes
Superseded. A later AD replaced this one: AD 2014-23-09. Comply with the one in force.
Model F.28 Mark 0100 series airplanes, certificated in any category; equipped with Messier-Dowty nose landing gear (NLG) having part number (P/N) 201071001 or 201071002, on which a main fitting subassembly (MFSA) having P/N 201071200, 201071228, 201071248, or 201071249 is installed.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (f) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently requires a one-time visual inspection and a one-time eddy current and/or dye penetrant inspection of the nose landing gear (NLG) main fitting to detect cracking; and rework of the NLG main fitting, if necessary. This amendment requires new inspections (one-time detailed visual inspection and repetitive eddy current or dye penetrant inspections) to detect cracking of the NLG main fitting subassembly, and corrective actions, if necessary. This amendment also revises the applicability of the existing AD. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flightcrew and passengers.
To prevent cracking of the NLG main fitting, which could lead to collapse of the NLG during takeoff and landing, and possible injury to the flightcrew and passengers, accomplish the following:
(a) Prior to the accumulation of 7,500 total flight cycles or within 50 flight cycles after the effective date of this AD, whichever occurs later: Perform a one-time detailed visual inspection of the NLG main fitting subassembly to detect cracking, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999.
(1) If no cracking is detected, no further action is required by this paragraph.
(2) If any cracking is detected, prior to further flight, accomplish the actions required by paragraph (b) of this AD.
Note 2: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirrors, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
Note 3: Actions accomplished prior to the effective date of this AD, in accordance with Fokker Service Bulletin SBF100-32-112, dated November 14, 1997, which was cited in AD 98-22-01, amendment 39-10847, are not considered acceptable for compliance with any requirements of this AD.
(b) Except as required by paragraph (a)(2) of this AD: Prior to the accumulation of 7,875 total flight cycles or within 375 flight cycles after the effective date of this AD, whichever occurs later, perform an eddy current or dye penetrant inspection of the NLG main fitting subassembly to detect cracking, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999. Such inspection within the compliance time required by paragraph (a) of this AD terminates the requirements of paragraph (a) of this AD. Repeat the inspection thereafter, using an eddy current or dye penetrant technique, at intervals not to exceed 750 flight cycles.
(c) If any cracking is detected during any inspection required by paragraph (b) of this AD: Prior to further flight, rework the main fitting of the NLG, in accordance with Part 3 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999. If, after rework, any cracking remains that exceeds the limits specified in the service bulletin, prior to further flight, accomplish the actions specified by either paragraph (c)(1) or (c)(2) of this AD.
(1) Replace the NLG in accordance with the service bulletin; and within 7,875 flight cycles after such replacement, perform the inspection as specified in paragraph (b) of this AD, and repeat the inspection thereafter at intervals not to exceed 750 flight cycles. Or
(2) Repair in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate; or the Rijksluchtvaartdienst (RLD) (or its delegated agent). For a repair method to be approved by the Manager, International Branch, ANM-116, as required by this paragraph, the Manager's approval letter must specifically reference this AD.
Note 4: The Fokker service bulletin references Messier-Dowty Service Bulletin F100-32-92, Revision 1, dated October 8, 1999, as an additional source of service information for accomplishing the inspections and rework of the NLG main fitting subassembly.
(d) Submit a report of the detailed visual inspection findings (positive and negative) required by paragraph (a) of this AD and a report of the initial eddy current or dye penetrant inspection findings (positive and negative) required by paragraph (b) of this AD to Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; at the applicable time specified in paragraph (d)(1) or (d)(2) of this AD. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMP) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501, et seq.) and have been assigned OMB Control Number 2120-0056.
(1) For airplanes on which the detailed visual inspection specified by paragraph (a) of this AD and the initial repetitive eddy current or dye penetrant inspection specified by paragraph (b) of this AD are accomplished after the effective date of this AD: Submit each report within 7 days after performing the applicable inspection.
(2) For airplanes on which the detailed visual inspection specified by paragraph (a) of this AD and the initial repetitive eddy current or dye penetrant inspection specified in paragraph (b) of this AD have been accomplished prior to the effective date of this AD: Submit the reports within 7 days after the effective date of this AD.
(e) As of the effective date of this AD, no person shall install a NLG having P/N 201071001 or 201071002 unless the installed MFSA has been inspected, by means of an eddy current or dye penetrant inspection, in accordance with paragraph (b) of this AD.
