AD 99-06-07 Airworthiness Directives; Short Brothers Model SD3-60 and SD3-60 SHERPA Series Airplanes

Models named: SD3-60, SD3-60 SHERPA series. Read the applicability below — it usually turns on serial or part numbers too.

All Model SD3-60 and SD3-60 SHERPA series airplanes, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For [[Page 12249]] 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 (d) 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 correct corrosion and/or wear of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the main landing gear (MLG), which could result in failure of the MLG to extend or retract, accomplish the following: (a) Within 90 days after the effective date of this AD, conduct an inspection for corrosion of the top and bottom shear decks of the left and right stub wings in the area of the forward pintle pin of the MLG, and measure the retaining pin holes of the pintle pin for wear; in accordance with Part A. of the Accomplishment Instructions of Short Brothers Service Bulletin SD360-53-42, dated September 1996 (for Model SD3-60 series airplanes), or Short Brothers Service Bulletin SD3-60 SHERPA-53-3, dated November 4, 1997 (for Model SD3- 60 SHERPA series airplanes), as applicable. (1) If no corrosion, wear, or discrepancy of the measurement of the holes for the retaining pin of the pintle pin is found, repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 6 months. (2) If any corrosion, wear, or measurement of the holes for the retaining pin of the pintle pin is found that is within the limits specified in Part A. of the Accomplishment Instructions of the applicable service bulletin, prior to further flight, repair the discrepancy in accordance with the applicable service bulletin. Thereafter, repeat the inspection required by paragraph (a) of this AD at intervals not to exceed 6 months. (3) If any corrosion, wear, or measurement of the holes for the retaining pin of the pintle pin is found that is beyond the limits specified in Part A. of the Accomplishment Instructions of the applicable service bulletin, prior to further flight, perform the actions required by paragraph (a)(3)(i) and (a)(3)(ii) of this AD. (i) Remove the corrosion and install bushings on the upper and lower shear webs in the retaining pin holes for the pintle pin in accordance with Part B. (left MLG) and/or Part C. (right MLG), as applicable, of the Accomplishment Instructions of the applicable service bulletin. (ii) Perform a visual inspection of the pintle pin and the sleeve for any discrepancy, in accordance with Part B. and/or Part C., as applicable, of the Accomplishment Instructions of the applicable service bulletin. (A) If no discrepancy is detected, the pintle pin and the sleeve of the pintle pin may be returned to service. (B) If any discrepancy of the pintle pin and sleeve is detected, prior to further flight, repair the pintle pin and sleeve or replace the pintle pin and sleeve with new or serviceable parts, in accordance with a method approved by either the Manager, International Branch, ANM-116, FAA, Transport Airplane Directorate, or the Civil Aviation Authority (CAA) (or its delegated agent). (b) Removal of corrosion and installation of bushings in accordance with Part B. and/or Part C., as applicable, of the Accomplishment Instructions of Short Brothers Service Bulletin SD360-53-42, dated September 1996 (for Model SD3-60 series airplanes), or Short Brothers Service Bulletin SD3-60 HERPA-53-3, dated November 4, 1997 (for Model SD3-60 SHERPA series airplanes), as applicable, constitutes terminating action for the repetitive inspection requirements of this AD. (c) For Model SD3-60 series airplanes: Replacement of the pin and circlip with a new pin and nut in accordance with Short Brothers Service Bulletin SD360-32-35, dated September 1996, constitutes terminating action for the repetitive inspection requirements of this AD. (d) 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. (e) 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. (f) Except as provided by paragraphs (a)(3)(ii)(B) and (c) of this AD, the actions shall be done in accordance with Short Brothers Service Bulletin SD360-53-42, dated September 1996, and Short Brothers Service Bulletin SD3-60 SHERPA-53-3, dated November 4, 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 Short Brothers, Airworthiness & Engineering Quality, P. O. Box 241, Airport Road, Belfast BT3 9DZ, Northern Ireland. 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 British airworthiness directives 005-09-96 and 005-11-97. (g) This amendment becomes effective on April 16, 1999. Issued in Renton, Washington, on March 4, 1999. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-5991 Filed 3-11-99; 8:45 am] BILLING CODE 4910-13-P