AD 97-24-11 Airworthiness Directives; Fokker Model F28 Mark 0100 Series Airplanes

Models named: F28 Mark 0100 series. Read the applicability below — it usually turns on serial or part numbers too.

Model F28 Mark 0100 series airplanes having the serial numbers specified in Table 1 of this AD; certificated in any category. Table 1.--Serial Numbers of Airplanes Subject to This AD ------------------------------------------------------------------------ ------------------------------------------------------------------------- 11244 through 11460, inclusive 11463 through 11469, inclusive 11471 11474 through 11483, inclusive 11489 through 11491, inclusive 11497 through 11499, inclusive 11501 11502 11504 11506 11507 11512 through 11515, inclusive 11517 11520 ------------------------------------------------------------------------ Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (e) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To detect and prevent fatigue cracking in the vertical stabilizer, which consequently could reduce its structural integrity, accomplish the following (a) For airplanes having serial numbers 11244 through 11419, inclusive, and 11421: Except as provided by paragraph (c) of this AD, prior to the accumulation of 8,500 total landings or within 30 days after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect fatigue cracking in the left-hand and right-hand flanges and finger strips at rib 5.0 of the vertical stabilizer, in accordance with Fokker Service Bulletin SBF100-55-019, Revision 1, dated May 19, 1993. (1) If no cracking is detected, repeat this inspection thereafter at intervals not to exceed 2,000 landings until the requirements of paragraph (b) of this AD are accomplished. (2) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate. (b) For airplanes with serial numbers 11244 through 11419 inclusive, and 11421, accomplish the requirements of both paragraphs (b)(1) and (b)(2) of this AD: (1) Except as provided by paragraph (c) of this AD, prior to the accumulation of 13,500 total landings, or within 6 months after the effective date of this AD, whichever occurs later, perform an eddy current inspection to detect fatigue cracking in the left-hand and right-hand flanges and finger strips at rib 5.0 of the vertical stabilizer, in accordance with Part 1 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-55-018, Revision 1, dated December 27, 1993. (i) If no cracking is detected, prior to further flight, accomplish the requirements of paragraph (b)(2) of this AD. (ii) If any cracking is detected, prior to further flight, repair in accordance with a method approved by the Manager, International Branch, ANM-116, and [[Page 63264]] accomplish the requirements of paragraph (b)(2) of this AD. (2) After accomplishing the requirements of paragraph (b)(1) of this AD, modify rib 5.0 of the vertical stabilizer by installing new stiffening, in accordance with Part 2 of the Accomplishment Instructions of Fokker Service Bulletin SBF100-55-018, Revision 1, dated December 27, 1993. Accomplishment of this modification constitutes terminating action for the repetitive inspections required by paragraph (a) of this AD. (c) The following exceptions apply with regard to the requirements of paragraphs (a) and (b) of this AD: (1) Accomplishment of the inspection specified in paragraph (a) and (b)(1) of this AD is not required if the modification specified in paragraph (b)(2) is accomplished prior to the accumulation of 7,300 total landings on the airplane. (2) Compliance with AD 91-18-15, amendment 39-8018, is not required if the requirements of paragraph (b)(2) of this AD are accomplished prior to the accumulation of 6,000 total landings on the airplane. (d) For all airplanes: At the applicable times specified in paragraph (d)(1) or (d)(2), modify the Hi-lok bolt holes at rib 5.0 of the vertical stabilizer by cold expansion, in accordance with Fokker Service Bulletin SBF100-55-023, dated January 3, 1995. (1) For airplanes that have been modified in accordance with the requirements of paragraph (b) of this AD prior to the effective date of this AD: Modify prior to the accumulation of either 10,000 landings after in-service modification, or 10,000 landings after delivery with factory modification, as applicable; or within 30 days after the effective date of this AD, whichever occurs later. (2) For all other airplanes: Modify concurrent with accomplishing the requirements of paragraph (b) of this AD. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The actions shall be done in accordance with the following Fokker service bulletins, which contain the following list of effective pages: ---------------------------------------------------------------------------------------------------------------- Referenced service bulletin Revision level shown on and date Page No. page Date shown on page ---------------------------------------------------------------------------------------------------------------- SBF100-55-018, Revision 1, 1-4, 8-16, 18, 19, 21- 1.......................... December 27, 1993. December 27, 1993. 23, 25-28. 5-7, 17, 20, 24, 29-31 Original................... May 19, 1993. SBF100-55-019, Revision 1, May 1-3, 5, 9,............ 1.......................... May 19, 1993. 19, 1993. 4, 6-8, 10-12......... Original................... August 11, 1992. SBF100-55-023, January 3, 1995 1-17.................. Original................... January 3, 1995. ---------------------------------------------------------------------------------------------------------------- This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Fokker Services B.V., Technical Support Department, P.O. Box 75047, 1117 ZN Schiphol Airport, The Netherlands. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Note 3: The subject of this AD is addressed in Dutch airworthiness directive (BLA) 93-069 (A), dated June 1, 1993. (h) This amendment becomes effective on January 2, 1998. Issued in Renton, Washington, on November 19, 1997. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 97-31029 Filed 11-26-97; 8:45 am] BILLING CODE 4910-13-P