AD 99-24-02 Airworthiness Directives; Boeing Model 767-200 and -300 Series Airplanes

Models named: 767-200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 767-200 and -300 series airplanes, as listed in Boeing Alert Service Bulletin 767-32A0185, dated September 2, 1999; 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 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 (f) 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 a fracture of the lower drag strut, which could result in collapse of the nose landing gear (NLG), accomplish the following: Visual Inspection (a) Within 90 days after the effective date of this AD, perform a one-time visual inspection to determine the part number and serial number of the lower drag strut of the NLG, in accordance with Boeing Alert Service Bulletin 767-32A0185, dated September 2, 1999. If the prefix of the serial number of the lower drag strut is not HM or FRG, no further action is required by this AD. Ultrasonic Inspection (b) For airplanes on which lower drag strut having part number (P/N) 162T2003-5 and serial number (S/N) prefix HM or FRG is installed: Prior to further flight, perform a one-time ultrasonic inspection to measure the wall thickness of the lower drag strut of the NLG, in accordance with Boeing Alert Service Bulletin 767- 32A0185, dated September 2, 1999, and accomplish paragraph (b)(1), (b)(2), or (b)(3) of this AD, as applicable, at the time specified. (1) If the wall thickness is greater than or equal to 0.210 inch: No further action is required by this AD. (2) If the wall thickness is greater than or equal to 0.180 inch, but less than 0.210 inch: Within 5 years after the effective date of this AD, overhaul the lower drag strut in accordance with Part 2 of the Accomplishment Instructions of the alert service bulletin. (3) If the wall thickness is less than 0.180 inch: Prior to further flight, replace the lower drag strut with a new or serviceable lower drag strut in accordance with Part 3 of the Accomplishment Instructions of the alert service bulletin. (c) For airplanes on which lower drag strut having P/N 162T2003- 1 or 162T2003-3 and S/N prefix HM or FRG is installed: Perform a one-time ultrasonic inspection to measure the wall thickness of the lower drag strut of the NLG, in accordance with Boeing Alert Service Bulletin 767-32A0185, dated September 2, 1999, and accomplish paragraph (c)(1), (c)(2), or (c)(3) of this AD, as applicable, at the time specified. (1) If the wall thickness is greater than or equal to 0.160 inch: No further action is required by this AD. (2) If the wall thickness is greater than or equal to 0.150 inch, but less than 0.160 inch: Within 5 years after the effective date of this AD, overhaul the lower drag strut in accordance with Part 2 of the Accomplishment Instructions of the alert service bulletin. (3) If the wall thickness is less than 0.150 inch: Prior to further flight, replace the lower drag strut with a new or serviceable lower drag strut in accordance with Part 3 of the Accomplishment Instructions of the alert service bulletin. (d) As of the effective date of this AD, no person shall install on any airplane, a lower drag strut of the NLG having P/N 162T2003- 1, 162T2003-3, or 162T2003-5, and S/N prefix HM or FRG, unless the part has been inspected to verify proper wall thickness in accordance with this AD. Reporting Requirement (e) Submit a report of the inspection findings (positive only, defined as a thin wall thickness condition that requires corrective action) to the Seattle Manufacturing Inspection District Office (MIDO), 2500 East Valley Road, Suite C-2, Renton, Washington 98055- 4056; fax (425) 227-1159; at the applicable time specified in paragraph (e)(1) or (e)(2) of this AD. The report must include the airplane serial number; the number of total flight hours and flight cycles on the airplane. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (1) For airplanes on which the applicable inspection required by either paragraph (b) or (c) of this AD is accomplished after the effective date of this AD: Submit the report within 30 days after performing the inspection. (2) For airplanes on which the applicable inspection required by either paragraph (b) or (c) of this AD has been accomplished prior to the effective date of this AD: Submit the report for the inspection within 30 days after the effective date of this AD. Alternative Methods of Compliance (f) 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, Seattle Aircraft Certification Office (ACO), 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, Seattle ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. Special Flight Permits (g) 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 (h) The actions shall be done in accordance with Boeing Alert Service Bulletin 767-32A0185, dated September 2, 1999. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-2207. 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. (i) This amendment becomes effective on December 6, 1999. Issued in Renton, Washington, on November 9, 1999. D.L. Riggin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 99-29822 Filed 11-18-99; 8:45 am] BILLING CODE 4910-13-U