Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300 Series Airplanes; and Model 747SP and 747SR Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3, and -7 Series Engines, 7052-7056 [05-2575]

Download as PDF 7052 Proposed Rules Federal Register Vol. 70, No. 27 Thursday, February 10, 2005 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20325; Directorate Identifier 2003–NM–129–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, and –300 Series Airplanes; and Model 747SP and 747SR Series Airplanes; Equipped With Pratt & Whitney Model JT9D–3, and –7 Series Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing transport category airplanes listed above. This proposed AD would require repetitive inspections for cracks of the upper surface of the aft lower spar web of the inboard and outboard struts, as applicable; and repetitive inspections for cracks of the upper surface of the intermediate web bay of the aft lower spar. This proposed AD would also require repetitive inspections and torque checks of the bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead for missing, loose, or fractured bolts, as applicable; and corrective action, if necessary. This proposed AD is prompted by reports of cracking in the aft lower spar web and reports of missing and fractured bolts. We are proposing this AD to detect and correct cracking of the aft lower spar web, and to prevent missing, loose, or fractured bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead, which could result in the loss of the aft lower spar load path and reduced structural capability of the pylon, which may VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 result in the separation of the engine from the airplane. DATES: We must receive comments on this proposed AD by March 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20325; the directorate identifier for this docket is 2003–NM–129–AD. FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6428; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20325; Directorate Identifier 2003–NM–129–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. Examining the Docket You can examine the AD docket 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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion We have received several reports of cracking in the aft lower spar web on Boeing Model 747–200B series airplanes equipped with Pratt & Whitney Model JT9D–7 series engines. The cracking in the aft lower spar web is the result of fatigue and sonic induced vibration. We also received reports of missing or fractured bolts common to the aft lower spar chord and the fitting of the rear engine mount bulkhead on Model 747– 100 series airplanes. The missing and fractured bolts were found on strut No. 1, No. 3 and No. 4. The missing and fractured bolts are made of Maraging or H–11 steel and are subject to stress corrosion cracking. These conditions, if not corrected, could result in the loss of the aft lower spar load path and reduced structural capability of the pylon, which may result in the separation of the engine from the airplane. The subject area on Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–3 series engines is identical to that on the E:\FR\FM\10FEP1.SGM 10FEP1 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules affected Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–7 series engines. Therefore, those Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–3 series engines are subject to the unsafe condition revealed on the affected Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–7 series engines. In addition, the subject area on Model 747–100B, –100B SUD, –200C, –200F, and –300 series airplanes, and Model 747SP and 747SR series airplanes, equipped with Pratt & Whitney Model JT9D–3 and –7 series engines, is identical to that on the affected Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–3 and –7 series engines. Therefore, those Model 747–100B, –100B SUD, –200C, –200F, and –300 series airplanes; and Model 747SP and 747SR series airplanes equipped with Pratt & Whitney Model JT9D–3 and –7 series engines are subject to the unsafe condition revealed on the affected Model 747–100 and –200B series airplanes equipped with Pratt & Whitney Model JT9D–3 and –7 series engines. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003, which describes the following procedures: 1. Part 1—Web Inspection For certain airplanes, do initial and repetitive detailed visual inspections of the upper surface of the aft lower spar web on the inboard struts, and outboard struts as applicable, for cracks. Do repairs, if necessary, and/or do ‘‘Part 4— Stiffener Addition.’’ 2. Part 2—Intermediate Web Bay Inspection For certain airplanes, do initial and repetitive detailed visual inspections of the upper surface of the intermediate web bay of the aft lower spar for cracks, do repairs if necessary, and/or do ‘‘Part 5—Intermediate Stiffener Addition.’’ 3. Part 3—Maraging or H–11 Steel Bolt Inspection For certain airplanes, do initial and repetitive detailed visual inspections and torque checks of the bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead for missing, loose, or fractured bolts; and replace bolt with new bolt if necessary. Replacing the bolt in accordance with ‘‘Part 3’’ includes related investigative actions and VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 corrective action. The related investigative actions include high frequency eddy current (HFEC) inspections for cracks of the chord, web, and fitting and detailed visual inspections for corrosion of the hole in the fitting of the rear engine mount bulkhead. The corrective action specifies contacting the manufacturer if any crack or corrosion is found. 4. Part 4—Stiffener Addition (Optional) For certain airplanes, install stiffeners for inboard and outboard struts as applicable, do related investigative actions, and do repairs if necessary. The related investigative actions include HFEC inspections for cracks of the hole and around the aft fasteners of the fitting of the rear engine mount bulkhead. ‘‘Part 4—Stiffener Addition’’ procedures will either extend the repetitive inspection interval or end the repetitive inspections of ‘‘Part 1—Web Inspection.’’ 5. Part 5—Intermediate Stiffener Addition (Optional) For certain airplanes, installing stiffeners for inboard and outboard struts will end the repetitive inspections of ‘‘Part 2—Intermediate Web Bay Inspection.’’ Boeing Alert Service Bulletin 747–54A2212 refers to Boeing Service Bulletins 747–71–2188 and 747–54–2115, as additional sources of service information for accomplishment of the installation. 6. Part 6—Maraging or H–11 Steel Bolt Replacement For certain airplanes, replace all Maraging or H–11 steel bolts with new inconel bolts; do related investigative actions (includes HFEC inspections for cracks of the chord and web, the chord and the fitting of the rear engine mount bulkhead fitting and the pylon skin; and detailed visual inspections for corrosion of the pylon skin and the hole of the fitting of the rear engine mount bulkhead); and do corrective action (includes contacting the manufacturer if any crack, corrosion, or damage is found which cannot be removed within the oversize limit). Replacement of all bolts with new inconel bolts in accordance with ‘‘Part 6—Maraging or H–11 Steel Bolt Replacement’’ ends the repetitive inspections of ‘‘Part 3—Maraging or H– 11 Steel Bolt Inspection.’’ We have determined that accomplishing the actions specified in the service information will adequately address the unsafe condition. PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 7053 FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. Therefore, we are proposing this AD, which would require the following actions: • Repetitive inspections for cracks of the upper surface of the aft lower spar web on the inboard and outboard struts, as applicable. • Repetitive inspections for cracks of the upper surface of the intermediate web bay of the aft lower spar, as applicable. • Repetitive inspections and torque checks of the bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead for missing, loose, or fractured bolts, as applicable. • Corrective action, if necessary. The proposed AD would require you to use the service information described previously to do these actions, except as discussed under ‘‘Differences Between the Proposed AD and the Service Bulletins.’’ Differences Between the Proposed AD and the Service Bulletins The following differences between the proposed AD and the service bulletins have been coordinated with the manufacturer: 1. Operators should note that although Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003, specifies that operators may contact the manufacturer for additional instructions for certain repairs, this proposed AD would require operators to repair according to a method approved by the FAA, or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the FAA to make those findings. 2. Operators should also note that where Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003, references ‘‘service bulletin 747–71– 2188 Revision 1 or later releases,’’ this proposed AD would require that operators refer to Boeing Service Bulletin 747–71–2188, Revision 1, dated January 17, 1986; or Revision 2, dated September 24, 1988. When referencing a specific service bulletin in an AD, using the phrase, ‘‘or later FAA-approved revisions,’’ violates Office of the Federal Register regulations for approving materials that are incorporated by reference. 3. Operators should also note, that where the referenced Boeing Service E:\FR\FM\10FEP1.SGM 10FEP1 7054 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules Bulletins 747–71–2188, Revision 1, dated January 17, 1986, and Revision 2, dated September 24, 1988; and Boeing Service Bulletins 747–54–2115, dated February 14, 1986, and Revision 1, dated May 12, 1988; specify to repair according to an operators equivalent procedure, this proposed AD would require operators to repair according to a method approved by the FAA, or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the FAA to make those findings. Clarification of Inspection Terminology In this proposed AD, the ‘‘detailed visual inspection’’ specified in Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003, is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. Costs of Compliance There are about 244 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 82 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Applicable airplanes identified in Boeing alert service bulletin 747–54A2212 as— Groups Groups Groups Groups 1–6 7–8 1–5 1–6 ..................................................... ..................................................... ..................................................... ..................................................... Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated 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 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 proposed AD. Action Web Inspection .............................................. Web Inspection .............................................. Web Bay Inspection ....................................... Bolt Inspection ................................................ 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 proposed 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–20325; Directorate Identifier 2003–NM–129–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by March 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 100, –100B, –100B SUD, –200B, –200C, –200F, and –300 series airplanes, and Model PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Average labor rate per hour Work hours 8 4 4 4 Cost per airplane, per inspection cycle $65 65 65 65 $520 260 260 260 747SP and 747SR series airplanes; certificated in any category; equipped with Pratt & Whitney Model JT9D–3 and –7 series engines; as identified in Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003. Unsafe Condition (d) This AD was prompted by reports of cracking in the aft lower spar web and reports of missing and fractured bolts. We are issuing this AD to detect and correct cracking of the aft lower spar web and to prevent missing, loose, or fractured bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead, which could result in the loss of the aft lower spar load path and reduced structural capability of the pylon, which may result in the separation of the engine from 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means Boeing Alert Service Bulletin 747–54A2212, dated May 1, 2003. Part 1—Web Inspections (g) At the applicable times specified in paragraph (g)(1), (g)(2), or (g)(3) of Table 1 of this AD, do initial and repetitive detailed inspections for cracks of the upper surface of the aft lower spar web of the inboard and outboard struts, as applicable; and before further flight, do any applicable repair; by doing all the actions specified in ‘‘Part 1— Web Inspection’’ of the Work Instructions of the service bulletin. For certain airplanes, the repetitive inspections may be deferred or ended provided that the optional stiffener addition specified in paragraph (k) 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 E:\FR\FM\10FEP1.SGM 10FEP1 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface 7055 cleaning and elaborate procedures may be required.’’ TABLE 1.—COMPLIANCE TIMES FOR WEB INSPECTION For Airplanes Identified in the Service Bulletin As— Initial Compliance Time Is— Repetitive Interval Is— (1) Group 1 airplanes on which the modification specified in Boeing Service Bulletin 747–54–2028, dated August 1, 1972, has been done; and Group 2 airplanes. (2) Group 1 airplanes on which the modification specified in Boeing Service Bulletin 747–54–2028, dated August 1, 1972, has not been done; and Group 7 airplanes. (3) Group 3, 4, 5, 6, and 8 airplanes ...................................................... Within 12 months after the effective date of this AD. At intervals not to exceed 2,400 flight cycles. Within 6 months after the effective date of this AD. At intervals not to exceed 350 flight cycles. Within 12 months after the effective date of this AD. At intervals not to exceed 1,200 flight cycles. Part 2—Intermediate Web Bay Inspection (h) At the applicable times specified in paragraph (h)(1) or (h)(2) of Table 2 of this AD, do initial and repetitive detailed inspections for cracks of the upper surface of the intermediate web bay of the aft lower spar; and before further flight do any applicable repair; by doing all the actions specified in ‘‘Part 2—Intermediate Web Bay Inspection’’ of the Work Instructions of the service bulletin. The repetitive inspections may be ended provided that the optional intermediate stiffener addition specified in paragraph (l) of this AD is done. TABLE 2.—COMPLIANCE TIMES FOR INTERMEDIATE WEB BAY INSPECTIONS For Airplanes Identified in the Service Bulletin As— Initial Compliance Time Is— Repetitive Interval Is— (1) Group 1 through 4 airplanes on which the modification specified in Boeing Service Bulletin 747–71–2188, dated March 14, 1983, has been done and on which the additional work specified in Boeing Service Bulletin AD 747–71–2188, Revision 1, dated January 17, 1986; or Revision 2, dated September 24, 1988; has not been done. (2) Group 5 airplanes on which the modification specified in Boeing Service Bulletin 747–54–2115, dated February 14, 1986; or Revision 1, dated May 12, 1988; has not been done. Within 6 months after the effective date of this AD. At intervals not to exceed 350 flight cycles. Within 6 months after the effective date of this AD. At intervals not to exceed 350 flight cycles. Part 3—Maraging or H–11 Steel Bolt Inspection (i) For Group 1 through 6 airplanes identified in the service bulletin: Within 12 months after the effective date of this AD, do a detailed inspection and torque check of the bolts common to the aft lower spar chords and the fitting of the rear engine mount bulkhead for missing, loose, or fractured bolts, and do any applicable replacement (including related investigative actions and corrective action), by doing all the actions specified in ‘‘Part 3 ‘‘Maraging or H–11 Steel Bolt Inspection’’ of the Work Instructions of the service bulletin, except as provided by paragraph (o) of this AD. Do any applicable replacements (including related investigative actions and corrective action) before further flight, except as provided by paragraph (j) of this AD. Repeat the actions thereafter at intervals not to exceed 18 months. The inspections and torque checks specified in paragraph (i) of this AD may be ended provided that the replacement specified in paragraph (n) of this AD is done. (j) If during any inspection required by paragraph (i) of this AD, one of the conditions specified in paragraphs (j)(1) and (j)(2) of this AD is found, do the applicable actions specified in paragraphs (j)(1) and (j)(2) of this AD. (1) If a missing or fractured bolt is found on the inboard strut in any one bay, within 36 months after replacing the bolt with a new bolt, do the replacement specified in paragraph (n) of this AD. VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 (2) If two or more missing or fractured bolts are found in any one bay, before further flight, do the replacement specified in paragraph (n) of this AD. Part 4—Optional Stiffener Addition (k) Except as provided by paragraph (o) of this AD, accomplishing the optional stiffener addition for the inboard and outboard struts, doing the related investigation actions, and doing any applicable repair, by doing all the actions specified in ‘‘Part 4—Stiffener Addition’’ of the Work Instructions of the service bulletin before further flight after accomplishing the actions specified in paragraph (g) of this AD, defers or ends the repetitive inspections required by paragraph (g) of this AD as follows: (1) For airplanes listed in paragraph (g)(2) of Table 1 of this AD, accomplishing the optional stiffener addition extends the repetitive inspections required by paragraph (g) of this AD to intervals not to exceed 2,400 flight cycles. (2) For airplanes listed in paragraph (g)(3) of Table 1 of this AD, accomplishing the optional stiffener addition ends the repetitive inspections required by paragraph (g) of this AD. Part 5—Optional Intermediate Stiffener Addition (l) For airplanes identified in paragraphs (h)(1) and (h)(2) of Table 2 of this AD: Accomplishing the optional intermediate stiffener addition for the inboard and outboard struts, by doing all the actions PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 specified in ‘‘Part 5—Intermediate Stiffener Addition’’ of the Work Instructions of the service bulletin before further flight after accomplishing the actions specified in paragraph (h) of this AD, except as provided by paragraph (m) of this AD, ends the repetitive inspections required by paragraph (h) of this AD. (m) Where the service bulletin specifies to install stiffeners as shown in ‘‘service bulletin 747–71–2188 Revision 1 or later releases (Group 1, 2,3, and 4 Airplanes) or 747–54–2115 Original Issue or Revision 1 (Group 5 Airplanes),’’ this AD requires that those actions be done in accordance with Boeing Service Bulletin 747–71–2188, Revision 1, dated January 17, 1986, or Revision 2, dated September 24, 1988; or Boeing Service Bulletin 747–54–2115, dated February 14, 1986, or Revision 1, dated May 12, 1988; as applicable, except as provided by paragraph (o) of this AD. Part 6—Maraging or H–11 Steel Bolt Replacement (n) For Group 1 through 6 airplanes identified in the service bulletin: Except as provided by paragraph (o) of this AD, replacing all Maraging or H–11 steel bolts with new inconel bolts, doing the related investigation actions, and doing any applicable corrective action, by doing all the actions specified in ‘‘Part 6—Maraging or H– 11 Steel Bolt Replacement’’ of the Work Instructions of the service bulletin ends the inspections and torque checks required by paragraph (i) of this AD. E:\FR\FM\10FEP1.SGM 10FEP1 7056 Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules Contact the FAA (o) If during any action required by this AD the service bulletin specifies to contact Boeing for additional instructions; or if Boeing Service Bulletin 747–71–2188, Revision 1, dated January 17, 1986, or Revision 2, dated September 24, 1988; or Boeing Service Bulletin 747–54–2115, dated February 14, 1986, or Revision 1, dated May 12, 1988, specifies to repair according to operators equivalent procedures: Before further flight, repair according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing 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 approval must specifically reference this AD. [Docket No. FAA–2005–20289; Directorate Identifier 2003–SW–55–AD] discovery of half-clamps that were incorrectly positioned. This condition, if not detected, could result in interference of the two half-clamps with the drive shaft, which could result in scoring on the drive shaft, failure of the drive shaft, and subsequent loss of control of the helicopter. DATES: Comments must be received on or before April 11, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically; • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically; • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590; • Fax: 202–493–2251; or • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053–4005, telephone (972) 641–3460, fax (972) 641–3527. You may examine the comments to this proposed AD in the AD docket on the Internet at https://dms.dot.gov. FOR FURTHER INFORMATION CONTACT: Eric Haight, Aviation Safety Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth, Texas 76193– 0111, telephone (817) 222–5204, fax (817) 222–5961. SUPPLEMENTARY INFORMATION: RIN 2120–AA64 Comments Invited Parts Installation (p) As of the effective date of this AD, no person may install a Maraging or H–11 steel bolt in the locations specified in this AD, on any airplane. Alternative Methods of Compliance (AMOCs) (q) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on January 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–2575 Filed 2–9–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Airworthiness Directives; Eurocopter France Model EC120 Helicopters Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC120 helicopters. This proposal would require inspecting the tail rotor drive shaft (drive shaft) damper halfclamps (half-clamps) to determine if they are centered on the friction ring, and if not correctly positioned, centering the half-clamps on the friction ring. This proposal is prompted by the VerDate jul<14>2003 16:17 Feb 09, 2005 Jkt 205001 We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2005–20289, Directorate Identifier 2003–SW–55–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit https://dms.dot.gov. Examining the Docket You may examine the docket that contains the proposed AD, any comments, and other information in person at the Docket Management System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone 1–800–647– 5227) is located at the plaza level of the Department of Transportation NASSIF Building in Room PL–401 at 400 Seventh Street, SW., Washington, DC. Comments will be available in the AD docket shortly after the DMS receives them. Discussion The Direction Generale De L’Aviation Civile (DGAC), the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Eurocopter Model EC120B helicopters. The DGAC advises of the discovery of a case of incorrect drive shaft damper positioning, which led to interference of the two half-clamps with the drive shaft tube and caused a score on the drive shaft. Eurocopter has issued Alert Telex No. 65A004, Revision 1, dated January 27, 2004, which specifies re-positioning of the drive shaft damper, if necessary. The DGAC classified this alert telex as mandatory and issued AD No. UF– 2003–465, dated December 22, 2003, and AD No. F–2003–465(A), dated January 21, 2004, to ensure the continued airworthiness of these helicopters in France. This helicopter model is manufactured in France and is type certificated for operation in the United States under the provisions of 14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the applicable bilateral agreement, the DGAC has kept us informed of the situation described above. We have examined the findings of the DGAC, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. E:\FR\FM\10FEP1.SGM 10FEP1

Agencies

[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7052-7056]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2575]

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Proposed Rules
Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.

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Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 /
Proposed Rules

[[Page 7052]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20325; Directorate Identifier 2003-NM-129-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD,
-200B, -200C, -200F, and -300 Series Airplanes; and Model 747SP and
747SR Series Airplanes; Equipped With Pratt & Whitney Model JT9D-3, and
-7 Series Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing transport category airplanes listed above. This
proposed AD would require repetitive inspections for cracks of the
upper surface of the aft lower spar web of the inboard and outboard
struts, as applicable; and repetitive inspections for cracks of the
upper surface of the intermediate web bay of the aft lower spar. This
proposed AD would also require repetitive inspections and torque checks
of the bolts common to the aft lower spar chords and the fitting of the
rear engine mount bulkhead for missing, loose, or fractured bolts, as
applicable; and corrective action, if necessary. This proposed AD is
prompted by reports of cracking in the aft lower spar web and reports
of missing and fractured bolts. We are proposing this AD to detect and
correct cracking of the aft lower spar web, and to prevent missing,
loose, or fractured bolts common to the aft lower spar chords and the
fitting of the rear engine mount bulkhead, which could result in the
loss of the aft lower spar load path and reduced structural capability
of the pylon, which may result in the separation of the engine from the
airplane.

DATES: We must receive comments on this proposed AD by March 28, 2005.

ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
By fax: (202) 493-2251.
Hand Delivery: room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m.
and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, PO Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://dms.dot.gov, or at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street SW., room PL-401, on
the plaza level of the Nassif Building, Washington, DC. This docket
number is FAA-2005-20325; the directorate identifier for this docket is
2003-NM-129-AD.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
917-6428; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-20325;
Directorate Identifier 2003-NM-129-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.

Examining the Docket

You can examine the AD docket 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 DOT street address stated in the ADDRESSES section.
Comments will be available in the AD docket shortly after the DMS
receives them.

Discussion

We have received several reports of cracking in the aft lower spar
web on Boeing Model 747-200B series airplanes equipped with Pratt &
Whitney Model JT9D-7 series engines. The cracking in the aft lower spar
web is the result of fatigue and sonic induced vibration. We also
received reports of missing or fractured bolts common to the aft lower
spar chord and the fitting of the rear engine mount bulkhead on Model
747-100 series airplanes. The missing and fractured bolts were found on
strut No. 1, No. 3 and No. 4. The missing and fractured bolts are made
of Maraging or H-11 steel and are subject to stress corrosion cracking.
These conditions, if not corrected, could result in the loss of the aft
lower spar load path and reduced structural capability of the pylon,
which may result in the separation of the engine from the airplane.
The subject area on Model 747-100 and -200B series airplanes
equipped with Pratt & Whitney Model JT9D-3 series engines is identical
to that on the

[[Page 7053]]

affected Model 747-100 and -200B series airplanes equipped with Pratt &
Whitney Model JT9D-7 series engines. Therefore, those Model 747-100 and
-200B series airplanes equipped with Pratt & Whitney Model JT9D-3
series engines are subject to the unsafe condition revealed on the
affected Model 747-100 and -200B series airplanes equipped with Pratt &
Whitney Model JT9D-7 series engines.
In addition, the subject area on Model 747-100B, -100B SUD, -200C,
-200F, and -300 series airplanes, and Model 747SP and 747SR series
airplanes, equipped with Pratt & Whitney Model JT9D-3 and -7 series
engines, is identical to that on the affected Model 747-100 and -200B
series airplanes equipped with Pratt & Whitney Model JT9D-3 and -7
series engines. Therefore, those Model 747-100B, -100B SUD, -200C, -
200F, and -300 series airplanes; and Model 747SP and 747SR series
airplanes equipped with Pratt & Whitney Model JT9D-3 and -7 series
engines are subject to the unsafe condition revealed on the affected
Model 747-100 and -200B series airplanes equipped with Pratt & Whitney
Model JT9D-3 and -7 series engines.

Relevant Service Information

We have reviewed Boeing Alert Service Bulletin 747-54A2212, dated
May 1, 2003, which describes the following procedures:

1. Part 1--Web Inspection

For certain airplanes, do initial and repetitive detailed visual
inspections of the upper surface of the aft lower spar web on the
inboard struts, and outboard struts as applicable, for cracks. Do
repairs, if necessary, and/or do ``Part 4--Stiffener Addition.''

2. Part 2--Intermediate Web Bay Inspection

For certain airplanes, do initial and repetitive detailed visual
inspections of the upper surface of the intermediate web bay of the aft
lower spar for cracks, do repairs if necessary, and/or do ``Part 5--
Intermediate Stiffener Addition.''

3. Part 3--Maraging or H-11 Steel Bolt Inspection

For certain airplanes, do initial and repetitive detailed visual
inspections and torque checks of the bolts common to the aft lower spar
chords and the fitting of the rear engine mount bulkhead for missing,
loose, or fractured bolts; and replace bolt with new bolt if necessary.
Replacing the bolt in accordance with ``Part 3'' includes related
investigative actions and corrective action. The related investigative
actions include high frequency eddy current (HFEC) inspections for
cracks of the chord, web, and fitting and detailed visual inspections
for corrosion of the hole in the fitting of the rear engine mount
bulkhead. The corrective action specifies contacting the manufacturer
if any crack or corrosion is found.

4. Part 4--Stiffener Addition (Optional)

For certain airplanes, install stiffeners for inboard and outboard
struts as applicable, do related investigative actions, and do repairs
if necessary. The related investigative actions include HFEC
inspections for cracks of the hole and around the aft fasteners of the
fitting of the rear engine mount bulkhead. ``Part 4--Stiffener
Addition'' procedures will either extend the repetitive inspection
interval or end the repetitive inspections of ``Part 1--Web
Inspection.''

5. Part 5--Intermediate Stiffener Addition (Optional)

For certain airplanes, installing stiffeners for inboard and
outboard struts will end the repetitive inspections of ``Part 2--
Intermediate Web Bay Inspection.'' Boeing Alert Service Bulletin 747-
54A2212 refers to Boeing Service Bulletins 747-71-2188 and 747-54-2115,
as additional sources of service information for accomplishment of the
installation.

6. Part 6--Maraging or H-11 Steel Bolt Replacement

For certain airplanes, replace all Maraging or H-11 steel bolts
with new inconel bolts; do related investigative actions (includes HFEC
inspections for cracks of the chord and web, the chord and the fitting
of the rear engine mount bulkhead fitting and the pylon skin; and
detailed visual inspections for corrosion of the pylon skin and the
hole of the fitting of the rear engine mount bulkhead); and do
corrective action (includes contacting the manufacturer if any crack,
corrosion, or damage is found which cannot be removed within the
oversize limit). Replacement of all bolts with new inconel bolts in
accordance with ``Part 6--Maraging or H-11 Steel Bolt Replacement''
ends the repetitive inspections of ``Part 3--Maraging or H-11 Steel
Bolt Inspection.''
We have determined that accomplishing the actions specified in the
service information will adequately address the unsafe condition.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require the following actions:
Repetitive inspections for cracks of the upper surface of
the aft lower spar web on the inboard and outboard struts, as
applicable.
Repetitive inspections for cracks of the upper surface of
the intermediate web bay of the aft lower spar, as applicable.
Repetitive inspections and torque checks of the bolts
common to the aft lower spar chords and the fitting of the rear engine
mount bulkhead for missing, loose, or fractured bolts, as applicable.
Corrective action, if necessary.
The proposed AD would require you to use the service information
described previously to do these actions, except as discussed under
``Differences Between the Proposed AD and the Service Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

The following differences between the proposed AD and the service
bulletins have been coordinated with the manufacturer:
1. Operators should note that although Boeing Alert Service
Bulletin 747-54A2212, dated May 1, 2003, specifies that operators may
contact the manufacturer for additional instructions for certain
repairs, this proposed AD would require operators to repair according
to a method approved by the FAA, or according to data meeting the
certification basis of the airplane approved by an Authorized
Representative for the Boeing Delegation Option Authorization
Organization who has been authorized by the FAA to make those findings.
2. Operators should also note that where Boeing Alert Service
Bulletin 747-54A2212, dated May 1, 2003, references ``service bulletin
747-71-2188 Revision 1 or later releases,'' this proposed AD would
require that operators refer to Boeing Service Bulletin 747-71-2188,
Revision 1, dated January 17, 1986; or Revision 2, dated September 24,
1988. When referencing a specific service bulletin in an AD, using the
phrase, ``or later FAA-approved revisions,'' violates Office of the
Federal Register regulations for approving materials that are
incorporated by reference.
3. Operators should also note, that where the referenced Boeing
Service

[[Page 7054]]

Bulletins 747-71-2188, Revision 1, dated January 17, 1986, and Revision
2, dated September 24, 1988; and Boeing Service Bulletins 747-54-2115,
dated February 14, 1986, and Revision 1, dated May 12, 1988; specify to
repair according to an operators equivalent procedure, this proposed AD
would require operators to repair according to a method approved by the
FAA, or according to data meeting the certification basis of the
airplane approved by an Authorized Representative for the Boeing
Delegation Option Authorization Organization who has been authorized by
the FAA to make those findings.

Clarification of Inspection Terminology

In this proposed AD, the ``detailed visual inspection'' specified
in Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003, is
referred to as a ``detailed inspection.'' We have included the
definition for a detailed inspection in a note in the proposed AD.

Costs of Compliance

There are about 244 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 82 airplanes of
U.S. registry. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Applicable airplanes identified in Average labor airplane, per
Boeing alert service bulletin 747- Action Work hours rate per hour inspection
54A2212 as-- cycle
----------------------------------------------------------------------------------------------------------------
Groups 1-6............................ Web Inspection.......... 8 $65 $520
Groups 7-8............................ Web Inspection.......... 4 65 260
Groups 1-5............................ Web Bay Inspection...... 4 65 260
Groups 1-6............................ Bolt Inspection......... 4 65 260
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

The FAA's authority to issue rules regarding aviation safety is
found in Title 49 of the United States Code. 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.
This rulemaking is promulgated 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 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
proposed AD.

Regulatory Findings

We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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]

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

Boeing: Docket No. FAA-2005-20325; Directorate Identifier 2003-NM-
129-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by March 28, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, -
200B, -200C, -200F, and -300 series airplanes, and Model 747SP and
747SR series airplanes; certificated in any category; equipped with
Pratt & Whitney Model JT9D-3 and -7 series engines; as identified in
Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003.

Unsafe Condition

(d) This AD was prompted by reports of cracking in the aft lower
spar web and reports of missing and fractured bolts. We are issuing
this AD to detect and correct cracking of the aft lower spar web and
to prevent missing, loose, or fractured bolts common to the aft
lower spar chords and the fitting of the rear engine mount bulkhead,
which could result in the loss of the aft lower spar load path and
reduced structural capability of the pylon, which may result in the
separation of the engine from 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.

Service Bulletin Reference

(f) The term ``service bulletin,'' as used in this AD, means
Boeing Alert Service Bulletin 747-54A2212, dated May 1, 2003.

Part 1--Web Inspections

(g) At the applicable times specified in paragraph (g)(1),
(g)(2), or (g)(3) of Table 1 of this AD, do initial and repetitive
detailed inspections for cracks of the upper surface of the aft
lower spar web of the inboard and outboard struts, as applicable;
and before further flight, do any applicable repair; by doing all
the actions specified in ``Part 1--Web Inspection'' of the Work
Instructions of the service bulletin. For certain airplanes, the
repetitive inspections may be deferred or ended provided that the
optional stiffener addition specified in paragraph (k) 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

[[Page 7055]]

irregularity. Available lighting is normally supplemented with a
direct source of good lighting at an intensity deemed appropriate.
Inspection aids such as mirrors, magnifying lenses, etc. may be
necessary. Surface cleaning and elaborate procedures may be
required.''

Table 1.--Compliance Times for Web Inspection
------------------------------------------------------------------------
Initial Compliance
For Airplanes Identified in the Time Is-- Repetitive
Service Bulletin As-- Interval Is--
------------------------------------------------------------------------
(1) Group 1 airplanes on which Within 12 months At intervals not
the modification specified in after the to exceed 2,400
Boeing Service Bulletin 747-54- effective date of flight cycles.
2028, dated August 1, 1972, has this AD.
been done; and Group 2
airplanes.
(2) Group 1 airplanes on which Within 6 months At intervals not
the modification specified in after the to exceed 350
Boeing Service Bulletin 747-54- effective date of flight cycles.
2028, dated August 1, 1972, has this AD.
not been done; and Group 7
airplanes.
(3) Group 3, 4, 5, 6, and 8 Within 12 months At intervals not
airplanes. after the to exceed 1,200
effective date of flight cycles.
this AD.
------------------------------------------------------------------------

Part 2--Intermediate Web Bay Inspection

(h) At the applicable times specified in paragraph (h)(1) or
(h)(2) of Table 2 of this AD, do initial and repetitive detailed
inspections for cracks of the upper surface of the intermediate web
bay of the aft lower spar; and before further flight do any
applicable repair; by doing all the actions specified in ``Part 2--
Intermediate Web Bay Inspection'' of the Work Instructions of the
service bulletin. The repetitive inspections may be ended provided
that the optional intermediate stiffener addition specified in
paragraph (l) of this AD is done.

Table 2.--Compliance Times for Intermediate Web Bay Inspections
------------------------------------------------------------------------
Initial Compliance
For Airplanes Identified in the Time Is-- Repetitive
Service Bulletin As-- Interval Is--
------------------------------------------------------------------------
(1) Group 1 through 4 airplanes Within 6 months At intervals not
on which the modification after the to exceed 350
specified in Boeing Service effective date of flight cycles.
Bulletin 747-71-2188, dated this AD.
March 14, 1983, has been done
and on which the additional
work specified in Boeing
Service Bulletin AD 747-71-
2188, Revision 1, dated January
17, 1986; or Revision 2, dated
September 24, 1988; has not
been done.
(2) Group 5 airplanes on which Within 6 months At intervals not
the modification specified in after the to exceed 350
Boeing Service Bulletin 747-54- effective date of flight cycles.
2115, dated February 14, 1986; this AD.
or Revision 1, dated May 12,
1988; has not been done.
------------------------------------------------------------------------

Part 3--Maraging or H-11 Steel Bolt Inspection

(i) For Group 1 through 6 airplanes identified in the service
bulletin: Within 12 months after the effective date of this AD, do a
detailed inspection and torque check of the bolts common to the aft
lower spar chords and the fitting of the rear engine mount bulkhead
for missing, loose, or fractured bolts, and do any applicable
replacement (including related investigative actions and corrective
action), by doing all the actions specified in ``Part 3 `` Maraging
or H-11 Steel Bolt Inspection'' of the Work Instructions of the
service bulletin, except as provided by paragraph (o) of this AD. Do
any applicable replacements (including related investigative actions
and corrective action) before further flight, except as provided by
paragraph (j) of this AD. Repeat the actions thereafter at intervals
not to exceed 18 months. The inspections and torque checks specified
in paragraph (i) of this AD may be ended provided that the
replacement specified in paragraph (n) of this AD is done.
(j) If during any inspection required by paragraph (i) of this
AD, one of the conditions specified in paragraphs (j)(1) and (j)(2)
of this AD is found, do the applicable actions specified in
paragraphs (j)(1) and (j)(2) of this AD.
(1) If a missing or fractured bolt is found on the inboard strut
in any one bay, within 36 months after replacing the bolt with a new
bolt, do the replacement specified in paragraph (n) of this AD.
(2) If two or more missing or fractured bolts are found in any
one bay, before further flight, do the replacement specified in
paragraph (n) of this AD.

Part 4--Optional Stiffener Addition

(k) Except as provided by paragraph (o) of this AD,
accomplishing the optional stiffener addition for the inboard and
outboard struts, doing the related investigation actions, and doing
any applicable repair, by doing all the actions specified in ``Part
4--Stiffener Addition'' of the Work Instructions of the service
bulletin before further flight after accomplishing the actions
specified in paragraph (g) of this AD, defers or ends the repetitive
inspections required by paragraph (g) of this AD as follows:
(1) For airplanes listed in paragraph (g)(2) of Table 1 of this
AD, accomplishing the optional stiffener addition extends the
repetitive inspections required by paragraph (g) of this AD to
intervals not to exceed 2,400 flight cycles.
(2) For airplanes listed in paragraph (g)(3) of Table 1 of this
AD, accomplishing the optional stiffener addition ends the
repetitive inspections required by paragraph (g) of this AD.

Part 5--Optional Intermediate Stiffener Addition

(l) For airplanes identified in paragraphs (h)(1) and (h)(2) of
Table 2 of this AD: Accomplishing the optional intermediate
stiffener addition for the inboard and outboard struts, by doing all
the actions specified in ``Part 5--Intermediate Stiffener Addition''
of the Work Instructions of the service bulletin before further
flight after accomplishing the actions specified in paragraph (h) of
this AD, except as provided by paragraph (m) of this AD, ends the
repetitive inspections required by paragraph (h) of this AD.
(m) Where the service bulletin specifies to install stiffeners
as shown in ``service bulletin 747-71-2188 Revision 1 or later
releases (Group 1, 2,3, and 4 Airplanes) or 747-54-2115 Original
Issue or Revision 1 (Group 5 Airplanes),'' this AD requires that
those actions be done in accordance with Boeing Service Bulletin
747-71-2188, Revision 1, dated January 17, 1986, or Revision 2,
dated September 24, 1988; or Boeing Service Bulletin 747-54-2115,
dated February 14, 1986, or Revision 1, dated May 12, 1988; as
applicable, except as provided by paragraph (o) of this AD.

Part 6--Maraging or H-11 Steel Bolt Replacement

(n) For Group 1 through 6 airplanes identified in the service
bulletin: Except as provided by paragraph (o) of this AD, replacing
all Maraging or H-11 steel bolts with new inconel bolts, doing the
related investigation actions, and doing any applicable corrective
action, by doing all the actions specified in ``Part 6--Maraging or
H-11 Steel Bolt Replacement'' of the Work Instructions of the
service bulletin ends the inspections and torque checks required by
paragraph (i) of this AD.

[[Page 7056]]

Contact the FAA

(o) If during any action required by this AD the service
bulletin specifies to contact Boeing for additional instructions; or
if Boeing Service Bulletin 747-71-2188, Revision 1, dated January
17, 1986, or Revision 2, dated September 24, 1988; or Boeing Service
Bulletin 747-54-2115, dated February 14, 1986, or Revision 1, dated
May 12, 1988, specifies to repair according to operators equivalent
procedures: Before further flight, repair according to a method
approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA; or according to data meeting the certification basis of
the airplane approved by an Authorized Representative for the Boeing
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 approval must specifically reference this
AD.

Parts Installation

(p) As of the effective date of this AD, no person may install a
Maraging or H-11 steel bolt in the locations specified in this AD,
on any airplane.

Alternative Methods of Compliance (AMOCs)

(q) The Manager, Seattle ACO, FAA, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.

Issued in Renton, Washington, on January 26, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-2575 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P

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