Airworthiness directives › 2004-07-06
AD 2004-07-06 Airworthiness Directives; Boeing Model 707 and 720 Series Airplanes
Models named: 707, 720 series. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
Model 707 and 720 series airplanes, as listed in Boeing 707 Alert Service Bulletin A3509, dated June 13, 2002; certificated in any category.
Compliance
Required as indicated, unless accomplished previously. To detect and correct cracking and/or loss of the upper and lower barrel nuts and bolts that retain the aft trunnion support fitting, which could result in the collapse of the main landing gear upon landing, accomplish the following: Service Bulletin References (a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3509, dated June 13, 2002. Initial Inspection (b) Within 60 days after the effective date of this AD, for each main landing gear, perform the inspection specified in paragraph (b)(1) of this AD and the torque check specified in paragraph (b)(2) of this AD, in accordance with the service bulletin. (1) Perform a detailed inspection of the upper and lower barrel nuts and bolts that retain the aft trunnion support fitting for corrosion, cracks, and loose or missing nuts and bolts. (2) Torque check the upper and lower bolts to verify the torque is within the range specified in Figure 2 of the service bulletin. Repetitive Inspections (c) If no corrosion, crack, or loose or missing nut or bolt is found, and the torque is found to be within the specified range, during the inspection and torque check specified in paragraph (b) of this AD, then repeat the actions specified in paragraph (b) of this AD thereafter at intervals not to exceed 60 days. Corrective Actions (d) If any corrosion, crack, or loose or missing nut or bolt is found, or if the torque is found not to be within the specified range, during the inspection and torque check specified in paragraph (b) of this AD: Before further flight, do the corrective actions specified in paragraphs (d)(1) through (d)(3) of this AD. Accomplishment of these actions constitutes terminating action for the repetitive inspections specified in paragraph (c) of this AD. (1) Perform a detailed inspection of the aft trunnion bearing cap and aft trunnion support fitting for corrosion, in accordance with the service bulletin. If any corrosion is detected, before further flight, repair in accordance with the service bulletin. (2) Perform a magnetic particle inspection of the aft trunnion bearing cap for cracks in accordance with Figure 3 of the service bulletin. (i) If no crack is found, before further flight, reinstall the inspected aft trunnion bearing cap in accordance with the service bulletin. (ii) If any crack is found, before further flight, replace the aft trunnion bearing cap with a new aft trunnion bearing cap in accordance with the service bulletin. (3) Reinstall the main landing gear trunnion with new Inconel barrel nuts and bolts to retain the aft trunnion support fitting, in accordance with Figure 4 of the service bulletin. Terminating Action (e) Within one year after the effective date of this AD, for each main landing gear, replace the upper and lower steel barrel nuts and H-11 bolts that retain the aft trunnion support fitting with new Inconel barrel nuts and bolts as specified in paragraphs (d)(1) through (d)(3) of this AD. Accomplishment of these actions constitutes terminating action for the requirements of this AD. Parts Installation (f) As of the effective date of this AD, no person shall install a steel barrel nut with H-11 bolt to retain the aft trunnion support fitting, on any airplane. Alternative Methods of Compliance (g) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (h) The actions shall be done in accordance with Boeing 707 Alert Service Bulletin A3509, dated June 13, 2002. 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 Airplanes, 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. Effective Date (i) This amendment becomes effective on May 11, 2004. Issued in Renton, Washington, on March 19, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-7126 Filed 4-5-04; 8:45 am] BILLING CODE 4910-13-P
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