Airworthiness Directive · Amendment 39-14956 · Fokker Model F.28 Mark 0070 and 0100 Airplanes
Fokker Model F.28 Mark 0070 and 0100 Airplanes
This AD applies to Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category; equipped with any Dowty or Messier-Dowty main landing gear (MLG) listed in Table 1 of this AD.
| MLG part number (P/N)— | Equipped with sliding member P/N— |
|---|---|
| 201072011 | 201072301 or 201072305 |
| 201072012 | 201072301 or 201072305 |
| 201072013 | 201072301 or 201072305 |
| 201072014 | 201072301 or 201072305 |
| 201072015 | 201072301 or 201072305 |
| 201072016 | 201072301 or 201072305 |
The FAA is superseding an existing airworthiness directive (AD), which applies to certain Fokker Model F.28 Mark 0070 and 0100 airplanes. That AD currently requires a one-time inspection of the sliding members in the main landing gear (MLG) for cracking and replacement of the sliding members with serviceable parts if necessary. This new AD adds repetitive magnetic particle inspections of the sliding members of the MLG for cracking and corrective actions as necessary. This AD results from inspection findings that have shown repetitive inspections are needed to establish fleet safety. We are issuing this AD to detect and correct fatigue cracking of the sliding member, which could result in possible separation of the MLG from the airplane and consequent reduced controllability of the airplane upon landing and possible injury to passengers.
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 1,000 flight cycles or 6 months after May 19, 2004 (the effective date of AD 2004-08-01), whichever occurs first, perform a magnetic inspection of the sliding members of the MLG for cracking, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-133, dated April 1, 2002. If any crack is found during the inspection, before further flight, replace the sliding members with serviceable parts in accordance with the Accomplishment Instructions of the service bulletin.
Note 1: Fokker Service Bulletin SBF100-32-133, dated April 1, 2002, refers to Messier-Dowty Service Bulletin F100-32-103, dated March 11, 2002, as an additional source of service information.
As of May 19, 2004, no person may install a sliding member of the MLG, P/N 201072301 or P/N 201072305, on any airplane, unless it has been inspected in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-133, dated April 1, 2002; Fokker Service Bulletin SBF100-32-139, dated March 5, 2004; or Fokker Service Bulletin SBF100-32-144, dated September 19, 2005; and found to be serviceable.
Note 2: Fokker Service Bulletin SBF100-32-139, dated March 5, 2004, refers to Messier-Dowty Service Bulletin F100-32-105, dated March 2, 2004, as an additional source of service information for accomplishing a magnetic inspection.
Note 3: Fokker Service Bulletin SBF100-32-144, dated September 19, 2005, refers to Messier-Dowty Service Bulletin F100-32-110, dated August 25, 2005, as an additional source of service information for accomplishing a magnetic inspection.
Although Fokker Service Bulletin SBF100-32-133, dated April 1, 2002, specifies to submit certain information to the manufacturer, this AD does not include such a requirement.
(i) At the later of the compliance times specified in paragraphs (i)(1) and (i)(2) of this AD: Do a magnetic inspection of the sliding members of the left and right MLG for cracking, and do all corrective actions before further flight after the inspection, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Fokker Service Bulletin SBF100-32-144, dated September 19, 2005. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles.
(1) Within 2,000 flight cycles after accomplishing paragraph (f) of this AD.
(2) Within 4 months after the effective date of this AD.
Actions done before the effective date of this AD in accordance with Fokker Service Bulletin SBF100-32-139, dated March 5, 2004, are acceptable for compliance with the corresponding requirements of paragraph (f) of this AD.
