AD 2006-13-01 Airworthiness Directives; Boeing Model 727-200 Series Airplanes Equipped With a No. 3 Cargo Door

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

This AD applies to Boeing Model 727-200 series airplanes, certificated in any category, equipped with a No. 3 cargo door, as identified in Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Requirements of AD 86-17-05 R1 With Reduced Threshold and New Optional Inspection Method Inspections (f) At the earlier of the times specified in paragraphs (f)(1) and (f)(2) of this AD: Do a penetrant or detailed inspection of the forward frame of the No. 3 cargo door cutout for cracking, in accordance with paragraph C. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. After the effective date of this AD, the penetrant or detailed inspection must be done in accordance with paragraph 3.B.3. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. If any cracking is found, repair in accordance with paragraph (h) or (l) of this AD, as applicable. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) Within the next 300 flight cycles after September 3, 1987 (the effective date of AD 86-17-05 R1), or prior to accumulating 29,000 total flight cycles, whichever occurs later, unless accomplished within the last 1,900 flight cycles. (2) Prior to accumulating 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later. (g) At the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Do a detailed inspection of the forward frame of the No. 3 cargo door cutout for cracking, in accordance with paragraphs D. and E. of the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. After the effective date of this AD, the detailed inspection must be done in accordance with paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. If any cracking is found, repair in accordance with paragraph (h) or (l) of this AD, as applicable. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) Within the next 300 flight cycles after September 3, 1987, or prior to accumulating 35,000 total flight cycles, whichever occurs later, unless accomplished within the last 1,900 flight cycles. (2) Prior to accumulating 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later. Repair (h) Before further flight, repair any crack in the forward frame of the No. 3 cargo door cutout found before the effective date of this AD during any inspection required by paragraph (f) or (g) of this AD, in accordance with paragraph G. of the Accomplishment Instructions in Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. Repeat the inspections specified in paragraphs (f) and (g) of this AD at intervals not to exceed 2,200 flight cycles, for all areas of the forward frame not covered by the repair, in accordance with the Accomplishment Instructions of paragraphs C., D., and E. of Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986. New Requirements of This AD Inspection of Repairs of the Frame Done Before the Effective Date of the AD (i) For any repair to the forward frame of the No. 3 cargo door cutout done, as required by paragraph (h) of this AD, before the effective date of this AD: Within 18,000 flight cycles following the repair, or 2,200 flight cycles after the effective date of this AD, whichever occurs later, do a detailed inspection of the repair for cracking in accordance with the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. Thereafter, repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” New Inspections of Skin Surrounding the Frame (j) Prior to the accumulation of 18,000 total flight cycles, or within 2,200 flight cycles after the effective date of this AD, whichever occurs later: Do a penetrant or detailed inspection for cracking of the fuselage skin of the No. 3 cargo door cutout between stringers S-24 and S-27, in accordance with paragraph 3.B.3. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. Repeat the inspection at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. Repair of Cracked Skin (k) If any crack is found in the fuselage skin during any inspection required by paragraph (j) of this AD: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (p) of this AD. Repair of Cracked Frames and Post—Repair Inspections (l) If, after the effective date of this AD, any crack is found in the forward frame of the No. 3 cargo door cutout during any inspection required by paragraph (f), (g), or (i) of this AD: Before further flight, do the actions specified in paragraph (l)(1), (l)(2), or (l)(3) of this AD, as applicable. Inspect the repair within 18,000 flight cycles following the repair, in accordance with paragraphs 3.B.4. and 3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. Thereafter, repeat the inspections at intervals not to exceed 2,200 flight cycles, until the preventative modification specified in paragraph (n) of this AD is done. (1) If cracks have not severed the inner flange, do an interim repair using a method approved in accordance with the procedures specified in paragraph (p) of this AD. (2) Repair the crack in accordance with paragraph 3.B.7.b. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. (3) Replace the cracked segment of the frame with a new or serviceable component and install the frame reinforcement preventative modification, in accordance with paragraph 3.B.7.c. of the Accomplishment Instructions of Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002. This action terminates the requirements of this AD. Repairs Done According to Previous Issues of the Service Bulletin (m) Inspections and repairs done before the effective date of this AD in accordance with Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986; Boeing Service Bulletin 727-53A0169, Revision 3, dated June 11, 1987; Revision 4, dated January 21, 1988; and Revision 5, dated November 2, 1989, are acceptable for compliance with the corresponding requirements of paragraphs (h), (k), and (l) of this AD, as applicable. Terminating Modification Required by AD 90-06-09 (n) At the same time as the applicable inspections provided in paragraphs (f), (g), (i), and (j) of this AD are accomplished, doing the frame reinforcement preventative modification required by paragraph A. of AD 90-06-09 or the frame reinforcement preventative modification specified in Figure 2 of Boeing Service Bulletins 727-53A0169, Revision 5, dated November 2, 1989; and Revision 6, dated September 28, 2002; terminates the requirements of this AD. Paragraph A. of AD 90-06-09 references Boeing Document D6-54860, Revision C, dated December 11, 1989, “Aging Airplane Structural Modification Program—Model 727” as the appropriate source of service information for accomplishing the frame reinforcement preventative modification (along with numerous other structural modifications required by paragraph A. of AD 90-06-09). Information Submission (o) Although the service bulletins referenced in this AD specify to submit certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards 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 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. (4) An AMOC approved previously in accordance with AD 86-17-05 R1, is approved as an AMOC with the corresponding requirements and provisions of this AD. Material Incorporated by Reference (q) You must use Boeing Alert Service Bulletin 727-53A0169, Revision 2, dated May 23, 1986; or Boeing Service Bulletin 727-53A0169, Revision 6, dated September 28, 2002; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Boeing Alert Service Bulletin 727-53A0169, Revision 2, contains the following effective pages:   Page number Revision level shown on page Date shown on page 1, 3-16 2 May 23, 1986. 2 1 March 28, 1986. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at 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. Issued in Renton, Washington, on June 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-5498 Filed 6-19-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from additional reports of cracking in the forward frame of the No. 3 cargo door cutout. We are issuing this AD to detect and correct cracking of the forward frame and fuselage skin of the No. 3 cargo door cutout, which could result in failure of the frame and consequent rapid decompression of the airplane.