AD 2011-09-14 Airworthiness Directives; The Boeing Company Model 747-200B, -300, -400, -400D, and -400F Series Airplanes Powered by Pratt and Whitney 4000 or General Electric CF6-80C2 Series Engines

Models named: 747-200B, -300, -400, -400D, -400F series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to The Boeing Company Model 747-200B, -300, -400, -400D, and -400F series airplanes; certificated in any category; equipped with Pratt and Whitney 4000 or General Electric CF6-80C2 series engines, as identified in Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection To Determine if Correct Door Is Installed (g) Within 24 months after the effective date of this AD, do an inspection to determine if the correct mid-pivot access door is installed, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010. (h) If, during the inspection required by paragraph (g) of this AD, the correct mid-pivot door is found to be installed, before further flight, install a marker on the mid-pivot access door, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010. (i) If, during the inspection required by paragraph (g) of this AD, the correct mid-pivot door is not found to be installed, before further flight, do the actions required by paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010. (1) Rotate the mid-pivot bolt assembly to the correct orientation and replace the mid-pivot access door with a new or serviceable mid-pivot access door. (2) Install a marker on the mid-pivot access door. (3) Do the actions required by paragraph (i)(3)(i) or (i)(3)(ii) of this AD. (i) (Option 1) Do an ultrasonic inspection for cracking of the mid-pivot bolt assembly. (A) If no cracking is found, do the actions required by paragraphs (i)(3)(i)(A)( 1 ) and (i)(3)(i)(A)( 2 ) of this AD. ( 1 ) Repeat the ultrasonic inspection for cracking of the mid-pivot bolt assembly thereafter at intervals not to exceed 24 months until the action required by paragraph (i)(3)(i)(A)( 2 ) of this AD is done. ( 2 ) Within 60 months after the effective date of this AD, replace the mid-pivot bolt assembly with a new mid-pivot bolt assembly. Replacement terminates the repetitive inspections required by paragraph (i)(3)(i)(A)( 1 ) of this AD. (B) If any cracking is found, replace the mid-pivot bolt assembly with a new mid-pivot bolt assembly, before further flight. (ii) (Option 2) Replace the mid-pivot bolt assembly with a new mid-pivot bolt assembly. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov . (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Related Information (k) For more information about this AD, contact Kenneth Paoletti, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6434; fax (425) 917-6590; kenneth.paoletti@faa.gov . Material Incorporated by Reference (l) You must use Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-54A2232, dated April 15, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com . (3) You may review copies of the service information at the FAA, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on April 15, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-9919 Filed 4-29-11; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report that the left and right access doors of the spring beam mid-pivot bolt assembly for the No. 1 strut were inadvertently installed in the incorrect position during strut modification. The Federal Aviation Administration is issuing this AD to detect and correct incorrectly installed mid-pivot bolt assemblies on the spring beam on the outboard struts. Incorrectly installed bolt assemblies could lead to fatigue cracking and consequent fracturing of the mid-pivot bolt assembly, which could lead to loss of the spring beam load path and the possible separation of a strut and engine from the airplane during flight.