AD 2009-20-03 Airworthiness Directives; Boeing Model 727 Airplanes

Models named: 727, 727C, 727-100, 727-100C, 727-200, 727-200F series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category.

Comply with this AD within the compliance times specified, unless already done. Inspections and Corrective Actions (f) At the times specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008 (“the service bulletin”), except as provided by paragraphs (g), (h), (i), and (j) of this AD: Do the inspections to detect cracking of the left- and right-side web posts and shear ties of the kickload beam, by doing all of the actions specified in Part 2 and the applicable corrective actions specified in Part 3 of the Accomplishment Instructions of the service bulletin, except as provided by paragraph (k) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the intervals specified in paragraph 1.E. of the service bulletin. As an alternative to using the parts specified in Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, operators may fabricate their own parts in accordance with FAA-approved Boeing data. Clarifications and Exception to the Specified Compliance Times (g) To determine the compliance times for airplanes having exactly 52,000 total flight hours or 39,000 total flight cycles, for the purposes of this AD, these airplanes are grouped with airplanes having “less than” 52,000 total flight hours or 39,000 total flight cycles, as specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008. (h) Where Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (i) Where the “Condition” column of Table 1 of paragraph 1.E. of Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, refers to airplanes having accumulated the specified total flight hours and total flight cycles “at the date on this service bulletin,” this AD requires compliance for airplanes having accumulated the specified total flight hours and total flight cycles as of the effective date of this AD. (j) The “condition” in the first row of Table 1 of paragraph 1.E. of Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, applies to airplanes “with less than 52,000 total flight hours or 39,000 total flight cycles.” For this AD, the first row of Table 1 is applicable to airplanes “with less than 52,000 total flight hours and less than 39,000 total flight cycles.” Exception to the Specified Corrective Actions (k) If any cracking is found during any inspection required by this AD, and Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, specifies contacting Boeing for appropriate action: Before further flight, repair the cracking or damage using a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD. Alternative Methods of Compliance (AMOCs) (l)(1) The Manager, Seattle ACO, FAA, ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 917-6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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 an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who 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. Material Incorporated by Reference (m) You must use Boeing Special Attention Service Bulletin 727-55-0093, dated March 12, 2008, 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 this service information 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, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. (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 NARA, 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 September 15, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9-22871 Filed 9-28-09; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of cracking of the left- and right-side web posts and shear ties of the kickload beam. We are issuing this AD to detect and correct cracking of the left- and right-side web posts and shear ties of the kickload beam, which, when coupled with failures in the adjacent structure, could result in structural failure of the vertical stabilizer, and loss of control of the airplane.