Airworthiness Directive · Amendment 39-14399 · Fokker Model F27 Mark 050 Airplanes
Fokker Model F27 Mark 050 Airplanes
This AD applies to all Fokker Model F27 Mark 050 airplanes, certificated in any category.
The FAA is superseding an existing airworthiness directive (AD), which applies to all Fokker Model F27 Mark 050 series airplanes. The existing AD currently requires using a torque wrench to repetitively tighten the screws for the attachment of the leading edges of the elevators, rudder, and ailerons. This new AD requires the same actions as those of the existing AD, but with reductions in the intervals for repetitive actions. This AD also requires modifying the elevator, rudder, and aileron leading edge attachments with additional locking devices. This AD results from a report of an in-flight vibration caused by a loose leading edge section of the elevator. We are issuing this AD to prevent binding of the flight controls caused by loose attachment screws, which could result in reduced controllability of the airplane.
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 30 days after January 21, 2000 (the effective date of AD 99-27-13), use a torque wrench to tighten the screws for the attachment of the leading edges of the elevators in accordance with Fokker Service Bulletin SBF50-55-007, dated June 5, 1998; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 12 months until the initial tightening required by paragraph (i) of this AD is accomplished.
(g) Within 24 months after January 21, 2000, use a torque wrench to tighten the screws for the attachment of the leading edges of the rudder in accordance with Fokker Service Bulletin SBF50-55-009, Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 4,000 flight hours, or 24 months, whichever occurs first, until the initial tightening required by paragraph (j) of this AD is accomplished.
(h) Within 6 months after January 21, 2000, use a torque wrench to tighten the screws for the attachment of the leading edges of the ailerons in accordance with Fokker Service Bulletin SBF50-57-020, Revision 1, dated July 23, 1999; or Revision 2, dated June 17, 2002. After the effective date of this AD, only Revision 2 may be used. Repeat the tightening thereafter at intervals not to exceed 12 months until the initial tightening required by paragraph (k) of this AD is accomplished.
(i) Within 6 months after the effective date of this AD or 12 months after accomplishing the action in paragraph (f) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edges of the elevators in accordance with Fokker Service Bulletin SBF50-55-007, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 6 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (f) of this AD.
(j) Within 12 months after the effective date of this AD or 24 months after accomplishing the action in paragraph (g) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edge of the rudder in accordance with Fokker Service Bulletin SBF50-55-009, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 12 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (g) of this AD.
(k) Within 6 months after the effective date of this AD or 6 months after accomplishing the action in paragraph (h) of this AD, whichever occurs earlier: Use a torque wrench to tighten the screws for the attachment of the leading edges of the ailerons in accordance with Fokker Service Bulletin SBF50-57-020, Revision 2, dated June 17, 2002. Repeat the tightening thereafter at intervals not to exceed 6 months until the modification required by paragraph (l) of this AD is accomplished. Doing the actions in this paragraph terminates the repetitive actions of paragraph (h) of this AD.
At the earlier of the times in paragraph (l)(1) and (l)(2) of this AD, modify the elevator, rudder, and aileron leading edge attachments by installing additional locking devices in accordance with the Accomplishment Instructions of the service bulletins in Table 1 of this AD. Doing the modifications terminates the applicable repetitive actions in paragraphs (f), (g), (h), (i), (j), and (k) of this AD, as specified in Table 1.
(1) Within 24 months after the effective date of this AD.
(2) Within 180 months since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness.
| Fokker service bulletin | Location | Terminates the actions required in paragraph— |
|---|---|---|
| SBF50-55-008, Revision 3, dated June 17, 2002 | Elevator leading edge | (f) and (i). |
| SBF50-55-010, Revision 2, dated June 17, 2002 | Rudder leading edge | (g) and (j). |
| SBF50-57-021, Revision 2, dated June 17, 2002 | Aileron leading edge | (h) and (k). |
Note 1: Fokker Service Bulletin SBF50-55-010, Revision 2, refers to Fokker Service Bulletin SBF50-55-011, dated October 29, 2001, as an additional source of service information for modifying the rudder attachments. Fokker Service Bulletin SBF50-57-021, Revision 2, refers to Fokker Service Bulletin SBF50-57-025, dated October 29, 2001, as an additional source of service information for modifying the aileron attachments.
