AD 2003-23-01 Airworthiness Directives; Boeing Model 747-400, -400D, and -400F Series Airplanes

Models named: 747-400, -400D, -400F series. Read the applicability below — it usually turns on serial or part numbers too.

Model 747-400, -400D, and -400F series airplanes, as listed in Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct cracking in the yaw damper actuator portion of the upper and lower rudder power control module (PCM) main manifolds, which could result in an uncommanded left rudder hardover, consequent increased pilot workload, and possible runway departure upon landing, accomplish the following: Review of Airplane Maintenance Records (a) Within 3 months after the effective date of this AD: Review the airplane maintenance records to determine if each PCM has a main manifold with less than 15,000 total flight hours or fewer than 2,000 total flight cycles, or do the inspection required by paragraph (c) of this AD. Follow-on Actions: PCMs With a Main Manifold Having Less Than 15,000 Total Flight Hours or Less Than 2,000 Flight Cycles (b) If it can be positively determined from the review of the airplane maintenance records that each rudder PCM has a main manifold that is below either of the thresholds specified in paragraph (a) of this AD: Submit a report to the manufacturer in accordance with paragraph (d) of this AD. Follow-on Actions: PCMs With a Main Manifold Having 15,000 Total Flight Hours or More and 2,000 Flight Cycles or More (c) If it cannot be positively determined that each rudder PCM has a main manifold that is below either of the thresholds specified in paragraph (a) of this AD: Within 3 months after the effective date of this AD, do an ultrasonic inspection of the yaw damper actuator portion of the upper and lower rudder PCM main manifold in accordance with the Accomplishment Instructions specified in Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003. After completing the actions required by paragraph (c)(1) or (c)(2) of this AD, as applicable, submit a report to the manufacturer in accordance with paragraph (d) of this AD. (1) If no cracking is found: Apply sealant and a torque stripe and install a lockwire on the applicable rudder PCM per Figure 1 or Figure 2, as applicable, and the Accomplishment Instructions specified in Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003. (2) If any cracking is found: Before further flight, replace the affected PCM with a PCM with a main manifold having less than 15,000 total flight hours and less than 2,000 total flight cycles, or a PCM with a main manifold that has been inspected by the supplier (Parker Hannifin Corporation) or ultrasonically inspected in accordance with the Accomplishment Instructions specified in Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003. Reporting Requirements (d) At the applicable time specified in paragraph (d)(1) or (d)(2) of this AD, accomplish paragraph (e). (1) If the inspection was done after the effective date of this AD: Submit the report and PCM, if applicable, within 20 days after the inspection. (2) If the inspection was accomplished prior to the effective date of this AD: Submit the report and PCM, if applicable, within 20 days after the effective date of this AD. (e) Do the requirements of paragraphs (e)(1) and (e)(2) of this AD. 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) Submit a report of the airplane maintenance records review or the inspection findings (positive and negative) to: The Boeing Company, Service Engineering—Mechanical Systems, Attn: R. Adams, fax: (425) 342-5224. The report must contain the airplane and rudder PCM serial numbers, the total flight hours and flight cycles for each rudder PCM (and rudder PCM main manifold, if known), and a description of any damage found. Submission of the Inspection Report Form (Figure 3 of Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003) is an acceptable method of complying with this requirement. (2) Send parts to Parker Hannifin Corporation in accordance with the shipping instructions specified in Appendix A of the service bulletin. Parts Installation (f) As of the effective date of this AD, no person shall install on any airplane a rudder PCM with a main manifold having 15,000 total flight hours or more, or 2,000 total flight cycles or more, unless it has been ultrasonically inspected (either by the operator or the supplier) within the previous 15,000 flight hours or 2,000 flight cycles, in accordance with the Accomplishment Instructions specified in Boeing Alert Service Bulletin 747-27A2397, dated July 24, 2003. 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) Unless otherwise specified, the actions shall be done in accordance with Boeing Alert Service Bulletin 747-27A2397, dated July 24, 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, 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 December 18, 2003. Issued in Renton, Washington, on November 3, 2003. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 03-28089 Filed 11-12-03; 8:45 am] BILLING CODE 4910-13-P