AD/F2000/33 Amdt 1 Main Landing Gear Shock Absorber Restrictor (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/F2000/33 and issues the following AD under subregulation 39.001(1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Dassault Aviation Falcon 2000 Series Aeroplanes
| AD/F2000/33 Amdt 1 | Main Landing Gear - Shock Absorber Restrictor | 5/2009 |
Applicability: | DASSAULT AVIATION Falcon 2000 aircraft and all Falcon 2000EX aircraft (versions F2000DX and F2000EX EASy inclusive). |
Requirement: | 1. Update the operator’s approved aircraft maintenance programme (MP) to incorporate the applicable version of MP32-000 at revision date 06/2008 or later. 2. For MLG shock absorber with 4,200 Landings (LDG) or more, since new or since last overhaul at 15 January 2009 (the effective date of the original issue of this AD), inspect the shock absorber per the accomplishment instructions of SB F2000-366 or F2000EX-167, as applicable to aircraft model. If any damage is found, within the applicable time(s) or LDG limits specified in the relevant SB F2000-366 or F2000EX-167, repair the shock absorber per the accomplishment instructions of SB F2000-367 or F2000EX-185, as applicable to aircraft model. 3. For MLG shock absorber with 1,900 LDG or more, since new or since last overhaul at 15 January 2009 and installed on aeroplanes that have performed 6 Steep-approach landings or more, over the last 6 months before 15 January 2009, inspect the shock absorber per the accomplishment instructions of SB F2000-366 or F2000EX-167, as applicable to aircraft model. If any damage is found, within the applicable time(s) or LDG limits specified in the relevant SB F2000-366 or F2000EX-167, repair the shock absorber per the accomplishment instructions of SB F2000-367 or F2000EX-185, as applicable to aircraft model. Note 1: Steep Approach Standard Operating Procedures (SOPs) are found and defined in the Aeroplane Flight Manual (AFM) Appendices as listed in the Reference Publications. 4. For MLG shock absorber with 1,900 LDG or more, since new or since last overhaul at 15 January 2009 and installed on aeroplanes that have performed 5 Steep-approach landings or less, over the last 6 months before 15 January 2009, inspect the shock absorber per the accomplishment instructions of SB F2000-366 or F2000EX-167, as applicable to aircraft model. |
| If any damage is found, within the applicable time(s) or LDG limits specified in the relevant SB F2000-366 or F2000EX-167, repair the shock absorber per the accomplishment instructions of SB F2000-367 or F2000EX-185, as applicable to aircraft model. 5. For MLG shock absorber with less than 1,900 LDG since new or since last overhaul at 15 January 2009, inspect the shock absorber per the accomplishment instructions of SB F2000-366 or F2000EX-167, as applicable to aircraft model. If any damage is found, within the applicable time(s) or LDG limits specified in the relevant SB F2000-366 or F2000EX-167, repair the shock absorber per the accomplishment instructions of SB F2000-367 or F2000EX-185, as applicable to aircraft model. Embodiment of SB F2000-367 or F2000EX-185 without previous implementation of SB F2000-366 or F2000EX-167, as applicable to aircraft model, is acceptable to comply with Requirements 2, 3, 4, and 5 of this AD. 6. After accomplishment of Requirements 2, 3, 4 or 5 of this AD, and until further notice, repeat the shock absorber inspections and associated corrective actions per the accomplishment instructions of SB F2000-366 or F2000EX-167, as applicable to aircraft model. 7. Install or modify the LH and RH shock absorbers with P/N suffix as listed in table 1, and embodying M3120.
Note 2: M3120 can be complied with:
The modification leading to new Part Numbers as indicated in Table 1 terminates the repetitive inspection detailed in Requirement 6 of this AD. | ||||||||||||
| 8. Do not install on any aeroplane, a MLG shock absorber, as a replacement part, which does not have the appropriate part number suffix (e.g. -4..) as given in the above Table 1, as applicable to aircraft model. The use of later approved revisions of these Service Bulletins is acceptable for compliance with the requirements of this AD. Note 3: EASA AD 2009-0050 dated 5 March 2009 refers. This AD supersedes EASA AD 2008-0178. | |
Compliance: | For Requirement 1 - Remains unchanged as detailed in the original issue of this AD as: Within 3 months after 15 January 2009, unless previously accomplished. For Requirements 2 and 3 - Remains unchanged as detailed in the original issue of this AD as: Within 8 months after 15 January 2009, unless previously accomplished. For Requirement 4 - Remains unchanged as detailed in the original issue of this AD as: Within 18 months after the 15 January 2009 or before accumulation of 5,000 LDG since new or last overhaul for the MLG shock absorber, whichever occurs first. For Requirement 5 - Before accumulation of 3,000 LDG since new or last overhaul. For Requirement 6 - At intervals not to exceed 1,900 LDG. For Requirement 7 - Before accumulating 6,000 landings or 12 years, since new or since last overhaul, whichever occurs first, and unless previously accomplished. For Requirement 8 - From the effective date of this AD. |
| This Amendment becomes effective on 7 May 2009. | |
Background: | During the overhaul of a MLG of a Falcon 2000, the sleeve on the hydraulic flow restrictor in the shock absorber was found displaced because of the rupture of its three retaining screws. In this situation, the energy dissipation function of the shock absorber is lost and high loads may be transmitted to the aircraft structure during landing. Structural integrity may thus not be guaranteed over the entire certified landing conditions domain particularly in combination of high landing weight and high vertical speed. The failure of the retaining screws has been determined to be the final phase of a slow unscrewing process under normal operational conditions. The unsafe condition only exists once the three screws have failed. This AD requires a repetitive borescope inspection of the flow restriction system and, if necessary, repair of the shock absorber. This AD also mandates the update of the operator's maintenance programme to include a revision of the “Check after Hard Landing” MP calling for borescope inspection. |
| Amendment 1 introduces a terminating action to the repetitive inspections detailed in the AD. The terminating action is mandatory. The original issue of this AD became effective 15 January 2009. |
James Coyne
Delegate of the Civil Aviation Safety Authority
27 March 2009
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