AD 2003-26-01 Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes

Models named: 737-100, -200, -200C, -300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct loose bolts common to the flange of the rudder front spar and main thrust hinge and actuator assembly, as well as the auxiliary actuator support fitting, which could cause the rudder actuator to separate from the rudder during certain flight conditions, resulting in loss of rudder control and consequent loss of control of the airplane; accomplish the following: One-Time Inspection (a) For Groups 1, 2 and 3 airplanes, as listed in Boeing Alert Service Bulletin 737-55A1087, dated October 2, 2003: Within 120 days after the effective date of this AD, perform a one-time general visual inspection of the rudder assembly to determine if an aluminum/fiberglass rudder assembly (Group 1 airplanes), or, if a graphite rudder assembly, part number 65C27234-() or 65C25841-() (Group 2 and Group 3 airplanes) is installed; per the Work Instructions of Boeing Alert Service Bulletin 737-55A1087, dated October 2, 2003. Note 1: For the purposes of this AD, a general visual inspection is defined as: “A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.” (b) If an aluminum/fiberglass assembly is found: No further action is required by paragraph (c) of this AD. Stage 1—Repetitive Flange Bolt Inspections (c) If a graphite assembly is found: Within 120 days after the effective date of this AD, perform a general visual inspection of the flange bolts in the main thrust hinge and actuator assembly, as well as the auxiliary actuator support fitting to detect loose bolts, per “Stage 1—Repeat Flange Bolt Inspection” of the Work Instructions of Boeing Alert Service Bulletin 737-55A1087, dated October 2, 2003. (1) If no loose flange bolt is found: Repeat the inspection required by paragraph (c) of this AD at intervals not to exceed 1,500 flight cycles or 2,000 flight hours, whichever occurs first. (2) If any loose flange bolt is found: Before further flight, do the applicable corrective actions by accomplishing all actions specified in paragraphs 4. and 5. of “Stage 1—Repeat Flange Bolt Inspection” of the Work Instructions of the alert service bulletin. Thereafter, repeat the inspection required by paragraph (c) of this AD at intervals not to exceed 1,500 flight cycles or 2,000 flight hours, whichever occurs first. (d) For any aluminum/fiberglass rudder assembly having an identification plate indicating a graphite assembly, or for any graphite rudder assembly having an identification plate indicating an aluminum assembly, and the alert service bulletin specifies to contact Boeing for appropriate action: Prior to further flight, contact the Manager, Seattle Aircraft Certification Office (ACO), FAA; or a Boeing Company Designated Engineering Representative who has been authorized by the Manager, Seattle ACO, to make such findings. Parts Installation (e) As of the effective date of this AD, no person may install on any airplane a rudder assembly having part number 65C27234-() or 65C25841-(), unless it has been inspected per paragraph (c) of this AD. Information Submission (f) Although the service bulletin referenced in this AD specifies to submit inspection findings to the manufacturer, this AD does not include such a requirement. Alternative Methods of Compliance (g) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office (ACO), FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (h) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Alert Service Bulletin 737-55A1087, dated October 2, 2003. 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, PO 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 January 7, 2004. Issued in Renton, Washington, on December 12, 2003. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-31273 Filed 12-22-03; 8:45 am] BILLING CODE 4910-13-P