Airworthiness Directive · Amendment 39-18025 · Landing gear
Fokker Services B.V. Airplanes
This AD applies to Fokker Services B.V. Model F.28 Mark 0100 airplanes; certificated in any category; all serial numbers.
We are superseding Airworthiness Directive (AD) 2000-17-03 for all Fokker Services B.V. Model F.28 Mark 0100 airplanes. AD 2000-17- 03 required inspections of the nose landing gear (NLG) main fitting to detect cracking of the NLG main fitting subassembly, and corrective actions if necessary. This new AD retains the requirements of AD 2000- 17-03, requires installing a new part number NLG unit that terminates the repetitive inspections, and adds airplanes to the applicability. This AD was prompted by a report of an NLG main fitting failure. We are issuing this AD 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 flight crew and passengers.
This paragraph restates the actions required by paragraph (a) of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000). For airplanes equipped with a Messier-Dowty 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: Prior to the accumulation of 7,500 total flight cycles or within 50 flight cycles after October 3, 2000 (the effective date of AD 2000-17-03), 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 (i) of this AD.
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.
This paragraph restates the actions required by paragraph (b) of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), with a new exception. For airplanes equipped with a Messier-Dowty NLG having P/N 201071001 or 201071002, on which a MFSA having P/N 201071200, 201071228, 201071248, or 201071249 is installed: Except as required by paragraph (g)(2) of this AD, prior to the accumulation of 7,875 total flight cycles, or within 375 flight cycles after October 3, 2000 (the effective date of AD 2000-17-03), 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 the introductory text of paragraph (g) of this AD terminates the requirements of paragraph (g) of this AD. Repeat the inspection thereafter, using an eddy current or dye penetrant technique, at intervals not to exceed 750 flight cycles, except as required by paragraph (m)(1) of this AD. Repeat the inspection until the replacement specified in paragraph (l) of this AD is done, or the installation specified in paragraph (n) of this AD is done.
This paragraph restates the actions required by paragraph (c) of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), with revised repair methods. If any cracking is detected during any inspection required by paragraph (g) or (i) 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 Fokker Service Bulletin SBF100-32-118, dated October 8, 1999, prior to further flight, accomplish the actions specified by either paragraph (j)(1) or (j)(2) of this AD.
(1) Replace the NLG in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-118, dated October 8, 1999; and within 7,875 flight cycles after such replacement, perform the inspection as specified in paragraph (i) of this AD, and repeat the inspection thereafter at intervals not to exceed 750 flight cycles.
(2) Repair in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Rijksluchtvaartdienst (RLD) (or its delegated agent); or the European Aviation Safety Agency (EASA); or Fokker B.V. Service's EASA Design Organization Approval (DOA).
Note 1 to paragraph (j) of this AD: Fokker Service Bulletin SBF100-32-118, dated October 8, 1999, 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.
This paragraph restates the actions required by paragraph (d) of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), with revised contact information and minor editorial changes. Submit a report of the detailed visual inspection findings (positive and negative) required by paragraph (g) of this AD, and a report of the initial eddy current or dye penetrant inspection findings (positive and negative) required by paragraph (i) of this AD, to Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; or to Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 (0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com; at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. As of the effective date of this AD, submit reports to Fokker Services B.V., Technical Services Dept., P.O. Box 1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; fax +31 (0)88-6280-111; email technicalservices@fokker.com; Internet http://www.myfokkerfleet.com.
(1) For airplanes on which the detailed visual inspection specified by paragraph (g) of this AD, and the initial repetitive eddy current or dye penetrant inspection specified by paragraph (i) of this AD, are accomplished after October 3, 2000 (the effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000)): Submit each report within 7 days after performing the applicable inspection.
(2) For airplanes on which the detailed visual inspection specified by paragraph (g) of this AD, and the initial repetitive eddy current or dye penetrant inspection specified in paragraph (i) of this AD, have been accomplished prior to October 3, 2000 (the effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000)): Submit the reports within 7 days after October 3, 2000 (the effective date of AD 2000-17-03).
Except as provided by paragraph (m) of this AD, before the next scheduled main fitting overhaul of the NLG after the effective date of this AD, or within 36 months after the effective date of this AD, whichever occurs first: Replace all NLG units having P/N 201071001 with a new P/N 201071003 NLG unit, and replace all NLG units having P/N 201071002 with a new P/N 201071004 NLG unit, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker Manual Change Notification MCNM-F100-043, dated January 31, 2000.
For airplanes on which the next scheduled main fitting overhaul of the NLG is to occur later than 36 months after the effective date of this AD: Operators may accomplish the replacement required by paragraph (l) of this AD before the next scheduled main fitting overhaul of the NLG after the effective date of this AD, or within 72 months after the effective date of this AD, whichever occurs first, provided the actions specified in paragraphs (m)(1) and (m)(2) of this AD are done.
(1) Within 36 months after the effective date of this AD, accomplish the inspection specified in paragraph (i) of this AD within 750 flight cycles since the most recent inspection, and repeat thereafter at intervals not to exceed 375 flight cycles until the replacement specified in paragraph (l) of this AD is done or the installation specified in paragraph (n) of this AD is done.
(2) In addition to the inspection specified in paragraph (m)(1) of this AD, do all other on-condition actions specified in paragraph 1.E(1)(b) of Fokker Service Bulletin SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker Manual Change Notification MCNM-F100-043, dated January 31, 2000; except where Fokker Service Bulletin SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker Manual Change Notification MCNM-F100-043, dated January 31, 2000, specifies to contact Fokker Services B.V., before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Fokker Services B.V.'s EASA Design Organization Approval (DOA).
Note 2 to paragraph (m) of this AD: Fokker Service Bulletin SBF100-32-119, Revision 1, dated November 15, 2011, including Fokker Manual Change Notification MCNM-F100-043, dated January 31, 2000, references Messier-Dowty Service Bulletin F100-32-94, dated January 5, 2000, as an additional source of service information for replacing the NLG unit.
Installing a new P/N 201456001 or P/N 201461001 NLG unit, in accordance with Fokker Proforma Service Bulletin SBF100-32-149, Revision 1, dated October 25, 2007, including Appendix 1, dated December 12, 2006, is acceptable for compliance with the replacement required by paragraph (l) of this AD, provided the installation is accomplished within the compliance time specified in paragraph (l) of this AD; and, except for airplanes that comply with paragraph (m) of this AD, provided the installation is accomplished within the compliance time specified in paragraph (m) of this AD.
Prior to, or concurrently with, the installation of the NLG unit required by paragraph (l) of this AD or the optional installation specified in paragraph (n) of this AD, modify the NLG bracket, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-53-074, dated November 1, 1999.
Accomplishing the replacement specified in paragraph (l) of this AD or the installation specified in paragraph (n) of this AD terminates the repetitive eddy current or dye penetrant inspections required by paragraphs (i) and (m)(1) of this AD.
(1) For airplanes equipped with a Messier-Dowty NLG having P/N) 201071001 or 201071002, on which a main fitting subassembly (MFSA) having P/N 201071200, 201071228, 201071248, or 201071249 is installed: As of October 3, 2000 (the effective date of AD 2000-17-03, Amendment 39-11876 (65 FR 52298, August 29, 2000), and until the effective date of this AD, no person may install an NLG having P/N 201071001 or 201071002 unless the installed MFSA has been inspected by means of an eddy current or dye penetrant inspection, and corrected in accordance with paragraph (i) of this AD.
(2) For all airplanes: As of the effective date of this AD, no person may install an NLG having P/N 201071001 or 201071002 on any airplane.
