AD 99-18-04 Airworthiness Directives; Dornier Model 328-100 Series Airplanes

Models named: 328-100 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 328-100 series airplanes, serial numbers 3005, 3008, 3009, and 3011 through 3079 inclusive; except airplanes on which Dornier Service Bulletin SB-328-53-184, Revision 1, dated July 2, 1997, has been accomplished; certificated in any category. 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 (c) 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 prevent reduced structural integrity of the lower part of the main landing gear (MLG) fairing, and consequent separation of part of the fairing from the airplane and possible damgae to the airplane or injury to persons on the ground, accomplish the following: Inspections and Repairs (a) Within 300 hours time-in-service after the effective date of this AD, perform a visual inspection to detect cracking of the lower attachment flanges in the area of the bend radii of the forward and aft support beams of the MLG, in accordance with Dornier Alert Service Bulletin ASB-328-53-010, dated October 13, 1995. (1) If no cracking is found, repeat the inspection thereafter at intervals not to exceed 300 hours time-in-service, until the actions required by either paragraph (a)(2)(iii) or (b) of this AD have been accomplished. (2) If any cracking is found and the crack is less than 50 millimeters (1.97 inches) in length, accomplish paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of this AD. (i) Prior to further flight, accomplish stop drilling as a one- time temporary repair in accordance with the alert service bulletin. (ii) Repeat the inspection thereafter at intervals not to exceed 300 hours time-in-service until accomplishment of paragraph (a)(2)(iii) of this AD. If any inspection reveals that the cracking has grown beyond the stop drilled area, prior to further flight, accomplish paragraph (a)(2)(iii) of this AD. (iii) Within 6 months after the cracking is detected, accomplish the permanent repair in accordance with the alert service bulletin. Accomplishment of the permanent repair constitutes terminating action for the repetitive inspections required by this AD. (3) If any crack is found and the crack is greater than or equal to 50 millimeters (1.97 inches) in length, prior to further flight, accomplish the permanent repair in accordance with the alert service bulletin. Accomplishment of the permanent repair constitutes terminating action for the repetitive inspections by this AD. Terminating Modification (b) Within 3,000 hours time-in-service after the effective date of this AD, install reinforcement parts for the longitudinal beam of the MLG, in accordance wtih Dornier Service Bulletin SB-328-53-184, Revision 1, dated July 2, 1997. Accomplishment of this installation constitutes terminating action for the requirements of this AD. Alternative Methods of Compliance (c) 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, FAA, Transport Airplane Directorate. 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. Special Flight Permits (d) 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. Incorporation by Reference (e) The actions shall be done in accordance with Dornier Alert Service Bulletin ASB-328-53-010, dated October 13, 1995; and Dornier Service Bulletin SB-328-53-184, Revision 1, dated July 2, 1997. 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 Fairchild Dornier, Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. 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 German airworthiness directives 95-413, dated November 2, 1995, and 97-073, dated March 27, 1997. (f) This amendment becomes effective on October 6, 1999. Issued in Renton, Washington, on August 23, 1999. Vi L. Lipski, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-22390 Filed 8-31-99; 8:45 am] BILLING CODE 4910-13-M