Airworthiness Directive · Amendment 39-13710 · Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
Fokker Model F.28 Mark 0070 and 0100 Series Airplanes
Model F.28 Mark 0070 and 0100 series airplanes, certificated in any category, equipped with a Messier-Dowty main landing gear (MLG) unit having a part number (P/N) with a main fitting sub-assembly, as listed in Table 1 of this AD.
| P/N— | Which includes a Main fitting sub-assembly P/N— |
|---|---|
| 201072011 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
| 201072012 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
| 201072013 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
| 201072014 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
| 201072015 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
| 201072016 | 201072283, 201072284, or 201251258 (main fitting P/N 201072383, 201072384, or 201072389). |
This amendment supersedes an existing airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that currently requires repetitive inspections of certain main landing gear (MLG) main fittings to detect forging defects, and rework of the main fittings if necessary. This amendment requires either replacement of each MLG with a MLG that has main fittings that have been inspected and reworked, or various one-time inspections of the main fittings and rework if necessary. Either of these actions constitutes terminating action for the repetitive inspections. This action also revises the applicability by adding airplanes. The actions specified by this AD are intended to detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants. This action is intended to address the identified unsafe condition.
To detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants, accomplish the following:
(a) For Fokker Model F.28 Mark 0100 series airplanes: Before the accumulation of 1,000 total landings on a new MLG, or within 30 days after December 20, 2001 (the effective date of AD 2001-24-10, amendment 39-12527), whichever occurs later, do an initial eddy current inspection on all MLG main fittings to detect forging defects, per Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001. After accomplishment of the initial inspection, repeat the eddy current inspection thereafter at intervals not to exceed 500 landings or 6 months, whichever occurs first, per the service bulletin. Accomplishment of the actions required by paragraph (f) of this AD terminates the repetitive inspections. Although this service bulletin specifies to submit certain information to the part manufacturer, this AD does not include such a requirement.
(b) For Fokker Model F.28 Mark 0100 series airplanes: After any inspection required by paragraph (a) of this AD, before further flight, accomplish the applicable actions required by paragraph (b)(1) or (b)(2) of this AD.
(1) If any cracking is found within the limits specified in Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001: Rework the MLG main fitting per the service bulletin.
(2) If any cracking is found that exceeds the limits specified in Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001: Rework the MLG main fitting per a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Civil Aviation Authority—The Netherlands (CAA-NL) (or its delegated agent).
(c) During any action required by this AD, if the service bulletin specifies to contact Messier-Dowty for an appropriate action: Before further flight, repair per a method approved by the Manager, International Branch, ANM-116; or the CAA-NL (or its delegated agent).
(d) For Fokker Model F.28 Mark 0070 series airplanes: Before the accumulation of 1,000 total landings on a new MLG, or within 30 days after the effective date of this AD, whichever occurs later, do an initial eddy current inspection on all MLG main fittings to detect forging defects, per Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001. After accomplishment of the initial inspection, repeat the inspection thereafter at intervals not to exceed 500 landings or 6 months, whichever occurs first, per the service bulletin. Accomplishment of the actions required by paragraph (f) of this AD terminates the repetitive inspections.
(e) For Fokker Model F.28 Mark 0070 series airplanes: After any inspection required by paragraph (d) of this AD, before further flight, accomplish the applicable actions required by paragraph (e)(1) or (e)(2) of this AD.
(1) If any cracking is found within the limits specified in Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001: Rework the MLG main fitting per the service bulletin.
(2) If any cracking is found that exceeds the limits specified in Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001: Rework the MLG main fitting per a method approved by the Manager, International Branch, ANM-116; or the CAA-NL (or its delegated agent).
(f) For all airplanes: Before the accumulation of 16,000 total landings on a new MLG, do the actions in paragraph (f)(1) or (f)(2) of this AD. Accomplishment of paragraph (f)(1) or (f)(2) of this AD constitutes terminating action for the repetitive inspections required by paragraphs (a) and (d) of this AD.
(1) Replace the main fitting of the MLG with a main fitting that has had a detailed inspection to detect forging defects and has been reworked, per paragraph 2.B., Part 1, of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-134, dated March 24, 2003. Any discrepancy found during the detailed inspection must be repaired before further flight per a method approved by the Manager, International Branch, ANM-116; or the CAA-NL (or its delegated agent). Accomplishment of the applicable actions in the Fokker 100 Aircraft Maintenance Manual and Messier-Dowty Component Maintenance Manual, Chapter 32-11-04, is one approved method.
Note 1: For the purposes of this AD, a detailed 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 mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
Note 2: Fokker Service Bulletin SBF100-32-134, dated March 24, 2003, references Messier-Dowty Service Bulletin F100-32-102, including Appendices A, B, and C, dated February 24, 2003, as an additional source of service information for reworking the main fitting of each MLG.
(2) Do eddy current and etch penetrant inspections, as applicable, to detect forging defects; and rework the main fitting of each MLG, as applicable; by accomplishing all of the actions in paragraph 3.C. of the Accomplishment Instructions of Messier-Dowty Service Bulletin F100-32-102, including Appendices A, B, and C, dated February 24, 2003. Do all of the actions per the service bulletin. Any rework must be done before further flight.
(g) As of the effective date of this AD, no person may install a MLG, MLG main fitting sub-assembly, or MLG main fitting having a P/N listed in Messier-Dowty Service Bulletin F100-32-102, including Appendices A, B, and C, dated February 24, 2003, on any airplane unless the part has been inspected and reworked, as applicable, per that service bulletin.
(h) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.
(i) Unless otherwise specified in this AD, the actions shall be done in accordance with Fokker Service Bulletin SBF100-32-134, dated March 24, 2003; Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001; and Messier-Dowty Service Bulletin F100-32-102, including Appendices A, B, and C, dated February 24, 2003; as applicable.
(1) The incorporation by reference of Fokker Service Bulletin SBF100-32-134, dated March 24, 2003; and Messier-Dowty Service Bulletin F100-32-102, including Appendices A, B, and C, dated February 24, 2003; is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The incorporation by reference of Messier-Dowty Service Bulletin No. F100-32-101, including Appendices A and B, dated October 25, 2001, was approved previously by the Director of the Federal Register as of December 20, 2001 (66 FR 63159, December 5, 2001).
(3) Copies may be obtained from Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Note 3: The subject of this AD is addressed in Dutch airworthiness directive 2003-040, dated March 31, 2003.
