Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F Series Airplanes, 39647-39651 [05-13434]

Download as PDF Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations FR 34094, June 27, 2001), are approved as AMOCs for the inspection requirements of this AD only at fastener locations where the AMOC provided for installing either BACB30NX or BACB30US fasteners. Material Incorporated by Reference (q) You must use Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000; or Boeing Alert Service Bulletin 747– 57A2312, Revision 1, dated April 29, 2004; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approves the incorporation by reference of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000, as of August 1, 2001 (66 FR 34094, June 27, 2001). (3) To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go 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 https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 29, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13432 Filed 7–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19679; Directorate Identifier 2003–NM–132–AD; Amendment 39–14184; AD 2005–14–07] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 727, 727C, 727–100, 727– 100C, 727–200, and 727–200F series VerDate jul<14>2003 12:58 Jul 08, 2005 Jkt 205001 airplanes. This AD requires repetitive inspections of the carriage attach fittings on the foreflaps of each wing for cracking and other discrepancies, and corrective actions if necessary. For certain airplanes, this AD also concurrently requires various other actions related to the subject area. This AD also provides for an optional terminating action for the repetitive inspection requirements and for an optional replacement that defers the repetitive inspections. This AD is prompted by reports of damaged or failed outboard foreflaps with a cracked or failed carriage attach fitting of the foreflap sequencing carriage. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane. DATES: This AD becomes effective August 15, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of August 15, 2005. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2004–19679; the directorate identifier for this docket is 2003–NM– 132–AD. FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz; Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for certain Boeing Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F series airplanes. That action, published in the Federal Register on November 24, 2004 (69 FR 68274), proposed to require repetitive inspections of the carriage attach fittings on the foreflaps of each wing for cracking and other discrepancies, and PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 39647 corrective actions if necessary. For certain airplanes, that action also proposed to concurrently require various other actions related to the subject area. That action also proposed an optional terminating action for the repetitive inspection requirements and an optional replacement that defers the repetitive inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. Support for Proposed AD One commenter, the airplane manufacturer, supports the proposed AD. Request To Revise Applicability One commenter requests that the applicability of the proposed AD refer to serial numbers (S/N) of the foreflap assembly rather than to the S/Ns of the affected airplanes. The commenter states that flight controls are often swapped from airplane to airplane to accommodate maintenance and overhaul requirements. The commenter believes that tracking the S/N of the foreflap assembly will ensure that all affected parts (including spares) are modified, reworked, or replaced. We do not agree. The foreflap assembly is part of the type design for the affected Model 727 airplanes. Our general policy is that, when an unsafe condition has been identified, the AD is issued so that it is applicable to the type-certificated airplane, not to an item that is part of the type design. Making the AD applicable to the airplane model ensures that operators of those airplanes will be notified directly of the unsafe condition and the action required to correct it. While it is assumed that an operator will know the models of airplanes that it operates, there is a potential that the operator will not know or be aware of specific items, such as a foreflap assembly, that are installed on its airplanes. Therefore, calling out the airplane model as the subject of the AD prevents ‘‘unknowing noncompliance’’ on the part of the operator. We have made no change in this regard to the AD. Request To Extend Compliance Time One commenter requests that the compliance time specified in paragraph (h) of the proposed AD be revised from 3,500 flight cycles to 4,500 flight cycles. The commenter states that the modification instructions in paragraph G. of Part II of the Accomplishment E:\FR\FM\11JYR1.SGM 11JYR1 39648 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations Instructions of Boeing Service Bulletin 727–27–133, Revision 1, dated May 9, 1972 (referred to in paragraph (k) of the proposed AD as the appropriate source of service information for accomplishing concurrent requirements) involve part replacement, and in order to maintain a C-check schedule, a retrofit program must be put in place. This retrofit program would be costly and time consuming. We do not agree. The commenter provides no technical justification for extending the compliance time for the inspection required by paragraph (h) of the AD. In developing an appropriate compliance time, we considered the safety issues as well as the recommendations of the airplane manufacturer, and the practical aspect of accomplishing the required actions within a period of time that corresponds to the normal scheduled maintenance for most affected operators. In light of these items, we have determined that the compliance time of within 3,500 flight cycles after the effective date of this AD in paragraph (h) of this AD is appropriate. However, paragraph (r) of this AD provides affected operators the opportunity to apply for an adjustment of the compliance time if the operator also presents data that justify the adjustment. Request To Revise Service Bulletin One commenter requests that Boeing Service Bulletin 727–27–133, Revision 1, dated May 9, 1972, be revised to include figures illustrating all dimensions to ensure accuracy and consistency with existing airplane maintenance manual (AMM) procedures. The commenter notes that in paragraph A.1. of Part I of the Accomplishment Instructions of the service bulletin, Chapter 27–51–0 of the AMM is specified as the source of service information for the ‘‘X dimension.’’ The commenter states that the AMM lists the dimension as ‘‘X2X1,’’ but not as ‘‘X dimension.’’ The commenter further states that there is no Boeing master AMM, and each operator’s AMM is a little different from the other operators’ AMMs; therefore, consistency has a big part to play in carrying out the service bulletin instructions. We do not agree. Chapter 27–51–0 of the AMM does illustrate ‘‘X dimension’’ in multiple locations (figures and tables). It also defines ‘‘X1 dimension’’ as ‘‘X dimension’’ for flaps in the up position and ‘‘X2 dimension’’ as ‘‘X dimension’’ for each flap position other than flaps up. We find no change is necessary to the AD in this regard. The same commenter also requests that Figure 1 of Boeing Service Bulletin 727–27–133 show the airload support roller in relation to the foreflap track for clarity purposes. The commenter states that illustrating the airload support roller with the track will help operators to better visualize the area while accomplishing paragraph H. of Part I of the Accomplishment Instructions of the service bulletin. We do not agree. Although additional details in Figure 1 would be helpful to operators, the service bulletin contains the necessary information for accomplishing the required actions. In addition, Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002, which is also referenced in this AD as an appropriate source of service information, shows the location of the airload support rollers. Therefore, we have made no change to the AD in this regard. Changes to Delegation Authority Boeing has received a Delegation Option Authorization (DOA). We have revised this final rule to delegate the authority to approve an alternative method of compliance for any repair required by this AD to the Authorized Representative (AR) for the Boeing DOA Organization rather than the Designated Engineering Representative (DER). In addition, we inadvertently omitted from paragraph (k)(1)(ii) of the proposed AD the following sentence: ‘‘For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD.’’ This language was included elsewhere in the proposed AD for accomplishing certain conditions in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an AR for the Boeing DOA Organization who has been authorized by the FAA to make those findings. Therefore, we have revised paragraph (k)(1)(ii) of the AD accordingly. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance There are about 1,292 airplanes of the affected design in the worldwide fleet. We estimate that 855 airplanes of U.S. registry will be affected by this AD. The average labor rate is $65 per work hour. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS For— Action All airplanes ............ Inspections of the carriage attach fittings Certain airplanes .... Certain airplanes .... Certain airplanes .... Installation of guide blocks ...................... Inspection of foreflap airload roller travel Modification of the inboard jackscrews on the outboard flap. Inspection of the entire track and of the track rib faces. Certain airplanes .... Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, VerDate jul<14>2003 12:58 Jul 08, 2005 Jkt 205001 Work hours Parts cost Cost 4 None ....................... 32 4 4 Free ........................ None ....................... Free ........................ $222,300, or $260 per airplane, per inspection cycle. $2,080 per airplane. $260 per airplane. $260 per airplane. 12 None ....................... $780 per airplane. Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: 39649 Applicability (c) This AD applies to Boeing Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F series airplanes, as listed in Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002; certificated in any category. I Unsafe Condition PART 39—AIRWORTHINESS DIRECTIVES (d) This AD was prompted by reports of damaged or failed outboard foreflaps with a cracked or failed carriage attach fitting of the foreflap sequencing carriage. We are issuing this AD to detect and correct fatigue cracking of the attach fittings of the foreflap carriage of the wings, which could result in partial or complete loss of the foreflap and consequent loss of controllability of the airplane. 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–14–07 Boeing: Amendment 39–14184. Docket No. FAA–2004–19679; Directorate Identifier 2003–NM–132–AD. Effective Date (a) This AD becomes effective August 15, 2005. Affected ADs (b) None. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections (f) Except as provided by paragraph (o) of this AD: Within 1,000 flight cycles after the effective date of this AD, and thereafter at intervals not to exceed 1,000 flight cycles, inspect as specified in paragraphs (f)(1) and (f)(2) of Table 1 of this AD in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002. Table 1 is as follows: TABLE 1.—INSPECTION REQUIREMENTS Requirements— Description— (1) Area to inspect .............................................. (2) Type of inspections ....................................... The two carriage attach fittings on the inboard and outboard foreflaps of each wing. (i) A detailed inspection to detect cracks and surface deviations on all edges, surfaces, and lug attachment fastener holes. (ii) A high frequency eddy current (HFEC) inspection to detect cracks at the lug attachment fastener holes. Crack or Surface Deviation Findings: Replacement (g) If any crack is detected or if any surface deviation beyond the limits specified in the service bulletin is detected during any inspection required by paragraph (f) of this AD, before further flight, replace the carriage attach fitting with a new, improved fitting or a new fitting having the same part number as the existing fitting, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002. Measurement and Associated Corrective Action(s) (h) Within 3,500 flight cycles after the effective date of this AD, inspect for interference between the carriage attach fitting and the carriage lug fitting, and do other related investigative actions by accomplishing all the actions specified in paragraph 3.C. and Figure 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, VerDate jul<14>2003 12:58 Jul 08, 2005 Jkt 205001 dated June 27, 2002. Do the actions in accordance with the service bulletin. (i) If any discrepancy is found during any action required by paragraph (h) of this AD, before further flight, accomplish applicable corrective action(s) (e.g., adding a shim or reworking the carriage attachment lug assembly) in accordance with paragraph 3.C. and Figure 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002. Where the service bulletin specifies to contact the manufacturer if rework of the improved fitting is required: Before further flight, rework in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, or in accordance with data meeting the type certification basis of the airplane approved by an Authorized Representative (AR) for the Boeing Delegation Option Authorization (DOA) Organization who has been authorized by the FAA to make such findings. For a repair method to be approved, the repair must meet the certification basis of the PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 airplane, and the approval must specifically reference this AD. Concurrent Requirements (j) For Model 727 airplanes listed in Boeing 727 Service Bulletin 57–59, Revision 1, dated September 27, 1965: Before or at the same time with the requirements of paragraph (h) of this AD, install guide blocks and bushings in the midflap ribs in accordance with the Accomplishment Instructions of the service bulletin. (k) For Model 727 airplanes listed in Boeing Service Bulletin 727–27–133, Revision 1, dated May 9, 1972: Before or at the same time with the requirements of paragraph (h) of this AD, do the actions specified in paragraphs (k)(1) and (k)(2) of this AD, as applicable. (1) For Groups I and II airplanes identified in the service bulletin: Do a one-time inspection of the airload support roller for travel on the foreflap track in accordance with Part I of the Accomplishment Instructions of the service bulletin. E:\FR\FM\11JYR1.SGM 11JYR1 39650 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations (i) If the airload support roller travels within the limits specified in the service bulletin, modify the control drum of the inboard flap and inboard jackscrews of the outboard flap, in accordance with Part II of the Accomplishment Instructions of the service bulletin. (ii) If the airload support roller travels beyond the limits specified in the service bulletin, repair in accordance with a method approved by the Manager, Seattle ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by an AR for the Boeing DOA Organization who has been authorized by the FAA to make such findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. (2) For Group III airplanes identified in the service bulletin: Modify the inboard jackscrews of the outboard flap (i.e., replacing the down stop at the inboard jackscrews of the outboard flap) in accordance with Part II of the Accomplishment Instructions of the service bulletin. (1) For Model 727 airplanes listed in Boeing 727 Service Bulletin 57–72, dated September 21, 1966: Before or at the same time with the requirements of paragraph (h) of this AD, do the actions specified in paragraphs (l)(1) through (l)(4) of this AD. (1) Chamfer the upper and lower flanges at the aft end of the foreflap tracks in accordance with the Accomplishment Instructions of the service bulletin. (2) Do a standard magnetic particle inspection of the entire foreflap tracks for cracks in accordance with the Accomplishment Instructions of the service bulletin. If any crack is detected, before further flight, repair in accordance with a method approved by the Manager, Seattle ACO, FAA; or in accordance with data meeting the type certification basis of the airplane approved by an AR for the Boeing DOA Organization who has been authorized by the FAA to make such findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. (3) Do a general visual inspection of the track rib faces at the front and rear spars to verify if the opening in the spars is flush with or clear of the plane of the rib faces, in accordance with the Accomplishment Instructions of the service bulletin. If the opening is not flush or clear with the plane, before further flight, rework the spar opening in accordance with the Accomplishment Instructions of the service bulletin. (4) Do a general visual inspection of the head or shank of bolts by securing the foreflap links to the foreflap tracks to verify if they protrude beyond the edge of the track flange in accordance with the Accomplishment Instructions of the service bulletin. If the head or shank of the bolts protrude beyond the edge of the track flange, before further flight, rework in accordance with the Accomplishment Instructions of the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is defined as: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ (m) For airplanes other than those identified in the service bulletins specified in paragraphs (j) through (l) of this AD: Before or at the same time with the requirements of paragraph (h) of this AD, do an inspection to verify if any of the parts listed in the ‘‘Spares Affected’’ paragraph of each service bulletin referenced in paragraphs (j) through (l) of this AD are installed on the airplane. If any part identified in that paragraph is found installed, before further flight, do the applicable corrective and investigative action(s) specified in paragraphs (j) through (1) of this AD. Page number Revision level shown on page 1, 12, 14–18, 27 ................................................. 2–11, 13, 19–26, 28 ........................................... 1 ....................................................................... Original ............................................................. Optional Terminating Actions (n) Replacement of the two carriage attach fittings on the inboard and outboard foreflaps of each wing with new, improved fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002; and accomplishment of the actions specified in paragraphs (j) through (m) of this AD, as applicable, before or concurrently with the replacement; constitutes terminating action for the requirements of this AD. Optional Deferral of Inspection (o) Replacement of the two carriage attach fittings on the inboard and outboard foreflaps of each wing with new fittings having the same part number as the existing fittings, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–57A0135, Revision 3, dated June 27, 2002; and accomplishment of the actions specified in paragraphs (j) through (m) of this AD, as applicable, before or concurrently with the replacement; defers the next inspection required by paragraph (f) of this AD for 10,000 flight cycles after the replacement. Thereafter, repeat the inspections required by paragraph (f) of this AD at intervals not to exceed 1,000 flight cycles. Credit for Previously Accomplished Service Bulletins (p) Installations accomplished before the effective date of this AD in accordance with Boeing 727 Service Bulletin 57–59, dated September 2, 1965, are acceptable for compliance with the requirements of paragraph (j) of this AD. (q) Inspections and modifications accomplished before the effective date of this AD in accordance with Boeing Service Bulletin 727–27–133, dated October 7, 1971, are acceptable for compliance with the requirements of paragraph (k) of this AD. Alternative Methods of Compliance (AMOCs) (r)(1) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, FAA, is authorized to approve alternative methods of compliance for this AD. (2) 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 AR for the Boeing DOA Organization who has been authorized by the FAA to make such findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically reference this AD. Material Incorporated by Reference (s) You must use the service bulletins identified in Table 2 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. Boeing Service Bulletin 727–27–133, Revision 1, dated May 9, 1972, contains the following list of effective pages: Date shown on page May 9, 1972. October 7, 1971. Boeing 727 Service Bulletin 57–59, Revision 1, dated September 27, 1965, contains the following list of effective pages: VerDate jul<14>2003 12:58 Jul 08, 2005 Jkt 205001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\11JYR1.SGM 11JYR1 Federal Register / Vol. 70, No. 131 / Monday, July 11, 2005 / Rules and Regulations 39651 Page number Revision level date shown on page Date shown on page 1, 4, 6 ................................................................. 2, 3, 5 ................................................................. 1 ....................................................................... Original ............................................................. September 27, 1965. September 2, 1965. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go 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 https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. TABLE 2.—MATERIAL INCORPORATED BY REFERENCE Service bulletin Boeing Boeing Boeing Boeing Revision level Alert Service Bulletin 727–57A0135 ............................................... Service Bulletin 727–27–133 .......................................................... 727 Service Bulletin 57–59 ............................................................. 727 Service Bulletin 57–72 ............................................................. Issued in Renton, Washington, on June 29, 2005. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–13434 Filed 7–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21463; Directorate Identifier 2005–CE–30–AD; Amendment 39– 14144; AD 2005–12–51] RIN 2120–AA64 Airworthiness Directives; Rockwell International (Aircraft Specification No. A–2–575 Previously Held by North American and Recently Purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT– 6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G Airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 Previously Held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; correction AGENCY: SUMMARY: This document makes a correction to Airworthiness Directive (AD) 2005–12–51, which was published in the Federal Register on June 21, 2005 (70 FR 35519), and applies to Rockwell International (Aircraft Specification No. A–2–575 previously held by North VerDate jul<14>2003 13:54 Jul 08, 2005 Jkt 205001 3 1 1 Original American and recently purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT–6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) airplanes. We incorrectly referenced the docket number as FAA–2005–24163 throughout the document. The correct docket number is FAA–2005–21463. This action corrects the regulatory text. DATES: The effective date of this AD remains June 23, 2005. FOR FURTHER INFORMATION CONTACT: Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: (562) 627–5232; facsimile: (562) 627–5210; email: fred.guerin@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On June 14, 2005, FAA issued AD 2005–12–51, Amendment 39–14144 (70 FR 35519, June 21, 2005), which applies to Rockwell International (Aircraft Specification No. A–2–575 previously held by North American and recently purchased by Boeing) Models AT–6 (SNJ–2), AT–6A (SNJ–3), AT–6B, AT– 6C (SNJ–4), AT–6D (SNJ–5), AT–6F (SNJ–6), BC–1A, SNJ–7, and T–6G airplanes; and Autair Ltd. (Aircraft Specification No. AR–11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT–16) airplanes. We incorrectly referenced the docket number as FAA–2005–24163 throughout the document. The correct docket number is FAA–2005–21463. This action corrects the regulatory text. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 Date June 27, 2002. May 9, 1972. September 27, 1965. September 21, 1966. This AD requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. Need for the Correction This correction is needed to ensure that any comments (any written relevant data, views, or arguments regarding this AD) made by the public are appropriately filed and to eliminate misunderstanding in the field. Correction of Publication Accordingly, the publication of June 21, 2005 (70 FR 35519), of Amendment 39–14144; AD 2005–12–51, which was the subject of FR Doc. 05–12151, is corrected as follows: I Starting on page 35519 through page 35523, replace all references to Docket No. FAA–2005–24163 with Docket No. FAA–2005–21463. I PART 39—[AMENDED] § 39.13 [Corrected] On page 35521, in section 39.13 [Amended], in paragraph 2, replace Docket No. FAA–2005–24163 with Docket No. FAA–2005–21463. I On page 35523, in section 39.13 [Amended], in paragraph (h), replace Docket No. FAA–2005–24163 with Docket No. FAA–2005–21463. I The effective date remains June 23, 2005. E:\FR\FM\11JYR1.SGM 11JYR1

Agencies

[Federal Register Volume 70, Number 131 (Monday, July 11, 2005)]
[Rules and Regulations]
[Pages 39647-39651]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-13434]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19679; Directorate Identifier 2003-NM-132-AD;
Amendment 39-14184; AD 2005-14-07]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-
200F series airplanes. This AD requires repetitive inspections of the
carriage attach fittings on the foreflaps of each wing for cracking and
other discrepancies, and corrective actions if necessary. For certain
airplanes, this AD also concurrently requires various other actions
related to the subject area. This AD also provides for an optional
terminating action for the repetitive inspection requirements and for
an optional replacement that defers the repetitive inspections. This AD
is prompted by reports of damaged or failed outboard foreflaps with a
cracked or failed carriage attach fitting of the foreflap sequencing
carriage. We are issuing this AD to detect and correct fatigue cracking
of the attach fittings of the foreflap carriage of the wings, which
could result in partial or complete loss of the foreflap and consequent
loss of controllability of the airplane.

DATES: This AD becomes effective August 15, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of August
15, 2005.

ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2004-19679; the directorate
identifier for this docket is 2003-NM-132-AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz; Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for certain Boeing Model 727, 727C, 727-100, 727-100C, 727-
200, and 727-200F series airplanes. That action, published in the
Federal Register on November 24, 2004 (69 FR 68274), proposed to
require repetitive inspections of the carriage attach fittings on the
foreflaps of each wing for cracking and other discrepancies, and
corrective actions if necessary. For certain airplanes, that action
also proposed to concurrently require various other actions related to
the subject area. That action also proposed an optional terminating
action for the repetitive inspection requirements and an optional
replacement that defers the repetitive inspections.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
submitted on the proposed AD.

Support for Proposed AD

One commenter, the airplane manufacturer, supports the proposed AD.

Request To Revise Applicability

One commenter requests that the applicability of the proposed AD
refer to serial numbers (S/N) of the foreflap assembly rather than to
the S/Ns of the affected airplanes. The commenter states that flight
controls are often swapped from airplane to airplane to accommodate
maintenance and overhaul requirements. The commenter believes that
tracking the S/N of the foreflap assembly will ensure that all affected
parts (including spares) are modified, reworked, or replaced.
We do not agree. The foreflap assembly is part of the type design
for the affected Model 727 airplanes. Our general policy is that, when
an unsafe condition has been identified, the AD is issued so that it is
applicable to the type-certificated airplane, not to an item that is
part of the type design. Making the AD applicable to the airplane model
ensures that operators of those airplanes will be notified directly of
the unsafe condition and the action required to correct it. While it is
assumed that an operator will know the models of airplanes that it
operates, there is a potential that the operator will not know or be
aware of specific items, such as a foreflap assembly, that are
installed on its airplanes. Therefore, calling out the airplane model
as the subject of the AD prevents ``unknowing non-compliance'' on the
part of the operator. We have made no change in this regard to the AD.

Request To Extend Compliance Time

One commenter requests that the compliance time specified in
paragraph (h) of the proposed AD be revised from 3,500 flight cycles to
4,500 flight cycles. The commenter states that the modification
instructions in paragraph G. of Part II of the Accomplishment

[[Page 39648]]

Instructions of Boeing Service Bulletin 727-27-133, Revision 1, dated
May 9, 1972 (referred to in paragraph (k) of the proposed AD as the
appropriate source of service information for accomplishing concurrent
requirements) involve part replacement, and in order to maintain a C-
check schedule, a retrofit program must be put in place. This retrofit
program would be costly and time consuming.
We do not agree. The commenter provides no technical justification
for extending the compliance time for the inspection required by
paragraph (h) of the AD. In developing an appropriate compliance time,
we considered the safety issues as well as the recommendations of the
airplane manufacturer, and the practical aspect of accomplishing the
required actions within a period of time that corresponds to the normal
scheduled maintenance for most affected operators. In light of these
items, we have determined that the compliance time of within 3,500
flight cycles after the effective date of this AD in paragraph (h) of
this AD is appropriate. However, paragraph (r) of this AD provides
affected operators the opportunity to apply for an adjustment of the
compliance time if the operator also presents data that justify the
adjustment.

Request To Revise Service Bulletin

One commenter requests that Boeing Service Bulletin 727-27-133,
Revision 1, dated May 9, 1972, be revised to include figures
illustrating all dimensions to ensure accuracy and consistency with
existing airplane maintenance manual (AMM) procedures. The commenter
notes that in paragraph A.1. of Part I of the Accomplishment
Instructions of the service bulletin, Chapter 27-51-0 of the AMM is
specified as the source of service information for the ``X dimension.''
The commenter states that the AMM lists the dimension as ``X2-X1,'' but
not as ``X dimension.'' The commenter further states that there is no
Boeing master AMM, and each operator's AMM is a little different from
the other operators' AMMs; therefore, consistency has a big part to
play in carrying out the service bulletin instructions.
We do not agree. Chapter 27-51-0 of the AMM does illustrate ``X
dimension'' in multiple locations (figures and tables). It also defines
``X1 dimension'' as ``X dimension'' for flaps in the up position and
``X2 dimension'' as ``X dimension'' for each flap position other than
flaps up. We find no change is necessary to the AD in this regard.
The same commenter also requests that Figure 1 of Boeing Service
Bulletin 727-27-133 show the airload support roller in relation to the
foreflap track for clarity purposes. The commenter states that
illustrating the airload support roller with the track will help
operators to better visualize the area while accomplishing paragraph H.
of Part I of the Accomplishment Instructions of the service bulletin.
We do not agree. Although additional details in Figure 1 would be
helpful to operators, the service bulletin contains the necessary
information for accomplishing the required actions. In addition, Boeing
Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002,
which is also referenced in this AD as an appropriate source of service
information, shows the location of the airload support rollers.
Therefore, we have made no change to the AD in this regard.

Changes to Delegation Authority

Boeing has received a Delegation Option Authorization (DOA). We
have revised this final rule to delegate the authority to approve an
alternative method of compliance for any repair required by this AD to
the Authorized Representative (AR) for the Boeing DOA Organization
rather than the Designated Engineering Representative (DER).
In addition, we inadvertently omitted from paragraph (k)(1)(ii) of
the proposed AD the following sentence: ``For a repair method to be
approved, the repair must meet the certification basis of the airplane,
and the approval must specifically reference this AD.'' This language
was included elsewhere in the proposed AD for accomplishing certain
conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an AR for the Boeing DOA
Organization who has been authorized by the FAA to make those findings.
Therefore, we have revised paragraph (k)(1)(ii) of the AD accordingly.

Conclusion

We have carefully reviewed the available data, including the
comments that have been submitted, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

There are about 1,292 airplanes of the affected design in the
worldwide fleet. We estimate that 855 airplanes of U.S. registry will
be affected by this AD. The average labor rate is $65 per work hour.
The following table provides the estimated costs for U.S. operators to
comply with this AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
For-- Action Work hours Parts cost Cost
----------------------------------------------------------------------------------------------------------------
All airplanes.................... Inspections of the 4 None................ $222,300, or $260
carriage attach per airplane, per
fittings. inspection cycle.
Certain airplanes................ Installation of 32 Free................ $2,080 per airplane.
guide blocks.
Certain airplanes................ Inspection of 4 None................ $260 per airplane.
foreflap airload
roller travel.
Certain airplanes................ Modification of the 4 Free................ $260 per airplane.
inboard jackscrews
on the outboard
flap.
Certain airplanes................ Inspection of the 12 None................ $780 per airplane.
entire track and of
the track rib faces.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for

[[Page 39649]]

safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

2005-14-07 Boeing: Amendment 39-14184. Docket No. FAA-2004-19679;
Directorate Identifier 2003-NM-132-AD.

Effective Date

(a) This AD becomes effective August 15, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, 727-200, and 727-200F series airplanes, as listed in Boeing
Alert Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002;
certificated in any category.

Unsafe Condition

(d) This AD was prompted by reports of damaged or failed
outboard foreflaps with a cracked or failed carriage attach fitting
of the foreflap sequencing carriage. We are issuing this AD to
detect and correct fatigue cracking of the attach fittings of the
foreflap carriage of the wings, which could result in partial or
complete loss of the foreflap and consequent loss of controllability
of the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Inspections

(f) Except as provided by paragraph (o) of this AD: Within 1,000
flight cycles after the effective date of this AD, and thereafter at
intervals not to exceed 1,000 flight cycles, inspect as specified in
paragraphs (f)(1) and (f)(2) of Table 1 of this AD in accordance
with the Accomplishment Instructions of Boeing Alert Service
Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Table 1 is as
follows:

Table 1.--Inspection Requirements
------------------------------------------------------------------------
Requirements-- Description--
------------------------------------------------------------------------
(1) Area to inspect.......... The two carriage attach fittings on the
inboard and outboard foreflaps of each
wing.
(2) Type of inspections...... (i) A detailed inspection to detect
cracks and surface deviations on all
edges, surfaces, and lug attachment
fastener holes.
(ii) A high frequency eddy current (HFEC)
inspection to detect cracks at the lug
attachment fastener holes.
------------------------------------------------------------------------

Crack or Surface Deviation Findings: Replacement

(g) If any crack is detected or if any surface deviation beyond
the limits specified in the service bulletin is detected during any
inspection required by paragraph (f) of this AD, before further
flight, replace the carriage attach fitting with a new, improved
fitting or a new fitting having the same part number as the existing
fitting, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June
27, 2002.

Measurement and Associated Corrective Action(s)

(h) Within 3,500 flight cycles after the effective date of this
AD, inspect for interference between the carriage attach fitting and
the carriage lug fitting, and do other related investigative actions
by accomplishing all the actions specified in paragraph 3.C. and
Figure 2 of the Accomplishment Instructions of Boeing Alert Service
Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Do the
actions in accordance with the service bulletin.
(i) If any discrepancy is found during any action required by
paragraph (h) of this AD, before further flight, accomplish
applicable corrective action(s) (e.g., adding a shim or reworking
the carriage attachment lug assembly) in accordance with paragraph
3.C. and Figure 2 of the Accomplishment Instructions of Boeing Alert
Service Bulletin 727-57A0135, Revision 3, dated June 27, 2002. Where
the service bulletin specifies to contact the manufacturer if rework
of the improved fitting is required: Before further flight, rework
in accordance with a method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA, or in accordance with data
meeting the type certification basis of the airplane approved by an
Authorized Representative (AR) for the Boeing Delegation Option
Authorization (DOA) Organization who has been authorized by the FAA
to make such findings. For a repair method to be approved, the
repair must meet the certification basis of the airplane, and the
approval must specifically reference this AD.

Concurrent Requirements

(j) For Model 727 airplanes listed in Boeing 727 Service
Bulletin 57-59, Revision 1, dated September 27, 1965: Before or at
the same time with the requirements of paragraph (h) of this AD,
install guide blocks and bushings in the midflap ribs in accordance
with the Accomplishment Instructions of the service bulletin.
(k) For Model 727 airplanes listed in Boeing Service Bulletin
727-27-133, Revision 1, dated May 9, 1972: Before or at the same
time with the requirements of paragraph (h) of this AD, do the
actions specified in paragraphs (k)(1) and (k)(2) of this AD, as
applicable.
(1) For Groups I and II airplanes identified in the service
bulletin: Do a one-time inspection of the airload support roller for
travel on the foreflap track in accordance with Part I of the
Accomplishment Instructions of the service bulletin.

[[Page 39650]]

(i) If the airload support roller travels within the limits
specified in the service bulletin, modify the control drum of the
inboard flap and inboard jackscrews of the outboard flap, in
accordance with Part II of the Accomplishment Instructions of the
service bulletin.
(ii) If the airload support roller travels beyond the limits
specified in the service bulletin, repair in accordance with a
method approved by the Manager, Seattle ACO, FAA; or in accordance
with data meeting the type certification basis of the airplane
approved by an AR for the Boeing DOA Organization who has been
authorized by the FAA to make such findings. For a repair method to
be approved, the repair must meet the certification basis of the
airplane, and the approval must specifically reference this AD.
(2) For Group III airplanes identified in the service bulletin:
Modify the inboard jackscrews of the outboard flap (i.e., replacing
the down stop at the inboard jackscrews of the outboard flap) in
accordance with Part II of the Accomplishment Instructions of the
service bulletin.
(1) For Model 727 airplanes listed in Boeing 727 Service
Bulletin 57-72, dated September 21, 1966: Before or at the same time
with the requirements of paragraph (h) of this AD, do the actions
specified in paragraphs (l)(1) through (l)(4) of this AD.
(1) Chamfer the upper and lower flanges at the aft end of the
foreflap tracks in accordance with the Accomplishment Instructions
of the service bulletin.
(2) Do a standard magnetic particle inspection of the entire
foreflap tracks for cracks in accordance with the Accomplishment
Instructions of the service bulletin. If any crack is detected,
before further flight, repair in accordance with a method approved
by the Manager, Seattle ACO, FAA; or in accordance with data meeting
the type certification basis of the airplane approved by an AR for
the Boeing DOA Organization who has been authorized by the FAA to
make such findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane, and the approval
must specifically reference this AD.
(3) Do a general visual inspection of the track rib faces at the
front and rear spars to verify if the opening in the spars is flush
with or clear of the plane of the rib faces, in accordance with the
Accomplishment Instructions of the service bulletin. If the opening
is not flush or clear with the plane, before further flight, rework
the spar opening in accordance with the Accomplishment Instructions
of the service bulletin.
(4) Do a general visual inspection of the head or shank of bolts
by securing the foreflap links to the foreflap tracks to verify if
they protrude beyond the edge of the track flange in accordance with
the Accomplishment Instructions of the service bulletin. If the head
or shank of the bolts protrude beyond the edge of the track flange,
before further flight, rework in accordance with the Accomplishment
Instructions of the service bulletin.

Note 1: For the purposes of this AD, a general visual inspection
is defined as: ``A visual examination of an interior or exterior
area, installation, or assembly to detect obvious damage, failure,
or irregularity. This level of inspection is made from within
touching distance unless otherwise specified. A mirror may be
necessary to enhance visual access to all exposed surfaces in the
inspection area. This level of inspection is made under normally
available lighting conditions such as daylight, hangar lighting,
flashlight, or droplight and may require removal or opening of
access panels or doors. Stands, ladders, or platforms may be
required to gain proximity to the area being checked.''

(m) For airplanes other than those identified in the service
bulletins specified in paragraphs (j) through (l) of this AD: Before
or at the same time with the requirements of paragraph (h) of this
AD, do an inspection to verify if any of the parts listed in the
``Spares Affected'' paragraph of each service bulletin referenced in
paragraphs (j) through (l) of this AD are installed on the airplane.
If any part identified in that paragraph is found installed, before
further flight, do the applicable corrective and investigative
action(s) specified in paragraphs (j) through (1) of this AD.

Optional Terminating Actions

(n) Replacement of the two carriage attach fittings on the
inboard and outboard foreflaps of each wing with new, improved
fittings, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 727-57A0135, Revision 3, dated June
27, 2002; and accomplishment of the actions specified in paragraphs
(j) through (m) of this AD, as applicable, before or concurrently
with the replacement; constitutes terminating action for the
requirements of this AD.

Optional Deferral of Inspection

(o) Replacement of the two carriage attach fittings on the
inboard and outboard foreflaps of each wing with new fittings having
the same part number as the existing fittings, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
727-57A0135, Revision 3, dated June 27, 2002; and accomplishment of
the actions specified in paragraphs (j) through (m) of this AD, as
applicable, before or concurrently with the replacement; defers the
next inspection required by paragraph (f) of this AD for 10,000
flight cycles after the replacement. Thereafter, repeat the
inspections required by paragraph (f) of this AD at intervals not to
exceed 1,000 flight cycles.

Credit for Previously Accomplished Service Bulletins

(p) Installations accomplished before the effective date of this
AD in accordance with Boeing 727 Service Bulletin 57-59, dated
September 2, 1965, are acceptable for compliance with the
requirements of paragraph (j) of this AD.
(q) Inspections and modifications accomplished before the
effective date of this AD in accordance with Boeing Service Bulletin
727-27-133, dated October 7, 1971, are acceptable for compliance
with the requirements of paragraph (k) of this AD.

Alternative Methods of Compliance (AMOCs)

(r)(1) In accordance with 14 CFR 39.19, the Manager, Seattle
ACO, FAA, is authorized to approve alternative methods of compliance
for this AD.
(2) 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 AR
for the Boeing DOA Organization who has been authorized by the FAA
to make such findings. For a repair method to be approved, the
repair must meet the certification basis of the airplane, and the
approval must specifically reference this AD.

Material Incorporated by Reference

(s) You must use the service bulletins identified in Table 2 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise. Boeing Service Bulletin 727-27-133,
Revision 1, dated May 9, 1972, contains the following list of
effective pages:

------------------------------------------------------------------------
Revision level
Page number shown on page Date shown on page
------------------------------------------------------------------------
1, 12, 14-18, 27................ 1................. May 9, 1972.
2-11, 13, 19-26, 28............. Original.......... October 7, 1971.
------------------------------------------------------------------------

Boeing 727 Service Bulletin 57-59, Revision 1, dated September
27, 1965, contains the following list of effective pages:

[[Page 39651]]

------------------------------------------------------------------------
Revision level
Page number date shown on page Date shown on page
------------------------------------------------------------------------
1, 4, 6......................... 1................. September 27,
1965.
2, 3, 5......................... Original.......... September 2, 1965.
------------------------------------------------------------------------

The Director of the Federal Register approves the incorporation
by reference of these documents in accordance with 5 U.S.C. 552(a)
and 1 CFR part 51. To get copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207. To view the AD docket, go to the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street,
SW., room PL-401, Nassif Building, Washington, DC. To review copies
of the service information, go 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 https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.

Table 2.--Material Incorporated by Reference
------------------------------------------------------------------------
Service bulletin Revision level Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin 3 June 27, 2002.
727-57A0135.
Boeing Service Bulletin 727-27- 1 May 9, 1972.
133.
Boeing 727 Service Bulletin 57- 1 September 27, 1965.
59.
Boeing 727 Service Bulletin 57- Original September 21, 1966.
72.
------------------------------------------------------------------------

Issued in Renton, Washington, on June 29, 2005.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-13434 Filed 7-8-05; 8:45 am]
BILLING CODE 4910-13-P

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