Airworthiness Directive · Amendment 39-17040 · 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, equipped with Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) main landing gear (MLG).
We are adopting a new airworthiness directive (AD) for certain 2-Fokker Services B.V.2-Model F.28 Mark 0100 airplanes. This AD was prompted by reports of failure of the main fitting on Messier-Dowty main landing gear (MLG) units due to fatigue cracking in the area of the filler and bleeder holes, and failure of the sliding member due to fatigue cracking at the area of the chrome run-out/lower radius of the sliding tube portion of the sliding member. This AD requires modification and re-identification of the MLG units, or replacement of the MLG unit with a modified one. We are issuing this AD to detect and correct fatigue cracking of the main fitting or sliding member on the MLG, which could lead to failure of the MLG and possibly loss of control of the airplane during landing rollout.
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 48 months after the effective date of this AD, do an inspection of the MLG to determine whether Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) MLG units having part number (P/N) 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 are installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number of the MLG unit can be conclusively determined from that review. If any of those part numbers is found, do the requirements of paragraph (h) of this AD.
If, during the inspection required by paragraph (g) of this AD, any Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) MLG units having P/N 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016 are found, within 48 months after the effective date of this AD, do the actions specified in paragraph (h)(1) or (h)(2) of this AD.
(1) Replace each MLG unit having P/N 201072011, 201072012, 201072013, 201072014, 201072015, or 201072016, with a MLG unit having P/N 201072017, P/N 201072019, or P/N 201072021 (for left-hand), as applicable; or P/N 201072018, P/N 201072020 or P/N 201072022 (for right-hand), as applicable; in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-155, dated July 23, 2009, and do the actions required in paragraph (j) of this AD.
(2) Modify and re-identify each affected MLG unit identified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin F100-32-112, dated July 17, 2009, and do the actions required in paragraph (j) of this AD.
As of the effective date of this AD, no person may install on any airplane a MLG unit having P/N 201072011, P/N 201072012, P/N 201072013, P/N 201072014, P/N 201072015, or P/N 201072016.
After accomplishing the actions required by paragraph (h) of this AD, before further flight, remove the airplane flight manual amendment and placard that were installed as required by AD 2008-20-03, Amendment 39-15682 (73 FR 56452, September 29, 2008).
Prior to or concurrently with the action (replacement or modification) required by paragraph (h) of this AD, accomplish the following actions:
(1) Install the torque link spacer with changed outer diameter, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-097, dated September 30, 1995.
(2) Remove, if installed, the water spray deflectors, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-132, dated December 5, 2001.
(3) Replace all P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/N AE99119E brake quick-disconnect couplings with improved units, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-156, Revision 1, dated June 29, 2009. Accomplishing the actions required by this paragraph terminates the requirements of AD 2010-21-12, Amendment 39-16472 (75 FR 63042, October 14, 2010), for that airplane only.
Accomplishing the actions required by paragraph (h) of this AD terminates the requirements of the following ADs for that airplane only: AD 98-06-26, Amendment 39-10404 (63 FR 13502, March 20, 1998); AD 98-13-32, Amendment 39-10623 (63 FR 34581, June 25, 1998); AD 2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 2007); and AD 2008-20-03, Amendment 39-15682 (73 FR 56452, September 29, 2008).
Accomplishing the actions required by paragraph (h) of this AD terminates the requirements of AD 2004-14-01, Amendment 39-13710 (69 FR 41391, July 9, 2004), for that airplane only.
