AD 2005-13-28 Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes

Models named: 777-200, -300 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 777-200 and -300 series airplanes; certificated in any category; line numbers 002 through 283 inclusive.

Required as indicated, unless accomplished previously. To prevent failure of the vertical tie rods supporting certain electrical racks and the center stowage bins, which could cause the center stowage bins or electrical racks to fall onto passenger seats below during an emergency landing, impeding an emergency evacuation or injuring passengers, accomplish the following: Inspection to Determine Weight and Placard Installation (a) For airplanes in the groups listed in the table under paragraph 3.B.1.b.(3) of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004: Within 60 months after the effective date of this AD, do the applicable actions in paragraphs (a)(1) and (a)(2) of this AD. (1) Install placards that show weight limits for electrical racks E7, E11, and E15; as applicable; per the Accomplishment Instructions of the service bulletin. (2) For each electrical rack on which a placard was installed per paragraph (a)(1) of this AD: At the applicable compliance time specified in paragraph (a)(2)(i) or (a)(2)(ii) of this AD, perform a one-time inspection and records review to determine the weight of equipment installed in that electrical rack. This records review and inspection must include determining what extra equipment, if any, has been installed in the subject rack of the airplane, performing a detailed inspection to determine whether this equipment is installed on the airplane, calculating the total weight of the installed equipment, and comparing that total to the weight limit specified on the placard installed per paragraph (a)(1) of this AD. If the weight is outside the limits specified in the placard to be installed per the service bulletin, before further flight, remove equipment from the rack to meet the weight limit specified in the placard. (i) For airplanes on which the actions required by paragraph (a)(1) of this AD were done before the effective date of this AD: Within 12 months after the effective date of this AD. (ii) For airplanes on which the actions required by paragraph (a)(1) of this AD are done after the effective date of this AD: Before further flight after installing the placards. Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” Inspection to Measure Exposed Thread and Corrective Actions (b) For airplanes in the groups listed in the table under paragraph 3.B.1.b.(1) of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004: Within 60 months after the effective date of this AD, perform a detailed inspection of the clevis end of the vertical support tie rod for the center stowage bin to measure the exposed thread, per the Accomplishment Instructions of the service bulletin. If the measurement of the exposed thread is outside the limits specified in Figure 2 of the service bulletin, before further flight, perform all corrective actions specified in steps 2 through 14 inclusive of Figure 2 of the service bulletin (including installing a threaded sleeve, torquing the jam nuts, inserting a pin in the witness hole to ensure that the witness hole is blocked by the clevis shank, and making any applicable adjustment of the clevis). Perform the corrective actions per the Accomplishment Instructions of the service bulletin, except as provided by paragraph (e) of this AD. Replacement of Tie Rods for Center Stowage Bin (c) For airplanes in Group 21, as listed in the Airplane Group column of the table under 3.B.1.b.(2) of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004: Within 60 months after the effective date of this AD, replace the vertical support tie rods for the center stowage bin with new improved tie rods (including replacing the existing tie rod with a new improved tie rod, torquing the jam nuts, inserting a pin in the witness hole to ensure that the witness hole is blocked by the clevis shank, and making any applicable adjustment of the clevis) by doing all actions specified in steps 1 through 8 of Figure 3 of the service bulletin. Do these actions per the Accomplishment Instructions of the service bulletin. Any required adjustment of the clevis must be done before further flight. Inspection to Determine Weight, Tie Rod Replacement, and Placard Installation (d) For airplanes in the groups listed in the table under paragraph 3.B.1.b.(4) of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004: Do the actions in paragraphs (d)(1), (d)(2), and (d)(3) of this AD. (1) Within 60 months after the effective date of this AD, replace the vertical support tie rods for electrical racks E9, E11, and E13 (including replacing the existing tie rods with new improved tie rods, replacing an existing tie rod clamp with a new improved tie rod clamp, performing a free-play inspection of certain electrical racks, adjusting jam nuts as applicable, performing a general visual inspection through the witness hole to make sure tie rod threads are visible, and making any applicable adjustment to ensure tie rod threads are visible) by doing all actions specified in Figures 5, 6, 7, and 9 of the service bulletin; as applicable. Do these actions per the Accomplishment Instructions of the service bulletin. Any required adjustment must be done before further flight. (2) Before further flight after accomplishing paragraph (d)(1) of this AD, install placards that show weight limits for electrical racks E9, E11, and E13; as applicable; per the Accomplishment Instructions of the service bulletin. (3) For each electrical rack on which a placard was installed per paragraph (d)(2) of this AD: At the applicable compliance time specified in paragraph (d)(3)(i) or (d)(3)(ii) of this AD, perform a one-time inspection and records check to determine the weight of equipment installed in that electrical rack. This records review and inspection must include determining what, if any, extra equipment has been installed in the subject racks of the airplane, performing a detailed inspection to determine that this equipment is installed on the airplane, calculating the total weight of the installed equipment, and comparing that total to the weight limit specified on the placard installed per paragraph (d)(2) of this AD. If the weight is outside the limits specified in the placard, before further flight, remove equipment from the rack to meet the weight limit specified in the placard. (i) For airplanes on which the actions required by paragraphs (d)(1) and (d)(2) of this AD were done before the effective date of this AD: Within 12 months after the effective date of this AD. (ii) For airplanes on which the actions required by paragraphs (d)(1) and (d)(2) of this AD are done after the effective date of this AD: Before further flight after installing the placards. Actions Accomplished Previously (e) Actions accomplished before the effective date of this AD per the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, dated January 25, 2001; or Revision 1, dated January 10, 2002; are acceptable for compliance with the corresponding actions required by this AD, provided that the additional actions specified in Part 2 or 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004, are accomplished within the compliance time specified in this AD. The weighing requirements in paragraphs (a)(2) and (d)(3) of this AD must be accomplished at the applicable times identified in those paragraphs. Alternative Methods of Compliance (f) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. Incorporation by Reference (g) Unless otherwise specified in this AD, the actions must be done in accordance with Boeing Special Attention Service Bulletin 777-25-0144, Revision 2, dated January 15, 2004. 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. To get copies of this service information, go to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Effective Date (h) This amendment becomes effective on August 1, 2005. Issued in Renton, Washington, on June 15, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-12510 Filed 6-24-05; 8:45 am] BILLING CODE 4910-13-P