Airworthiness Directives; Boeing Model 747 Airplanes, 5066-5070 [05-1794]

Download as PDF 5066 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules Issued in Renton, Washington, on January 21, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–1793 Filed 1–31–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20243; Directorate Identifier 2004–NM–153–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Boeing Model 747–100, –200, –300, and 747SP series airplanes. The existing AD currently requires certain inspections to find missing or alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings, and corrective actions if necessary. For airplanes with missing or alloy-steel fasteners, the existing AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for certain inspections. This proposed AD would expand the applicability to include additional airplane models and would require a new inspection to determine fastener material and to find missing or broken fasteners, and related investigative/corrective actions if necessary. This proposed AD is prompted by reports indicating that cracked fasteners made of A286 material were found on airplanes that had only fasteners made of A286 material installed in the area common to the diagonal brace underwing fittings. We are proposing this AD to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel or A286 taperlock fasteners, which could result in separation of the engine and strut from the airplane. DATES: We must receive comments on this proposed AD by March 18, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. VerDate jul<14>2003 14:57 Jan 31, 2005 Jkt 205001 • Government-wide Rulemaking Web Site: Go to http://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. • 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, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at http:// dms.dot.gov, or in person 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– 20243; the directorate identifier for this docket is 2004–NM–153–AD. FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6432; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20243; Directorate Identifier 2004–NM–153–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 http:// 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 our docket 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 the DOT’s complete Privacy Act PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit http:// dms.dot.gov. Examining the Docket You can examine the AD docket on the Internet at http://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 DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the DMS receives them. Discussion On June 19, 2001, we issued AD 2001–13–06, amendment 39–12286 (66 FR 34094, June 27, 2001), for certain Boeing Model 747–100, –200, –300, and 747SP series airplanes. That AD requires certain inspections to find missing or alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings; and corrective actions, if necessary. For airplanes with missing or alloy-steel fasteners, that AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for the repetitive inspection. That AD was prompted by a report indicating that broken taperlock fasteners (bolts) were found on the diagonal brace underwing fittings on the outboard strut at the Number 1 and Number 4 engine pylons on a Boeing Model 747–200 series airplane having titanium underwing fittings. We issued that AD to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel taperlock fasteners, which could result in separation of the engine and strut from the airplane. Actions Since Existing AD Was Issued Since we issued AD 2001–13–06, we have received reports indicating that fractured fasteners have been found on Model 747–200B series airplanes that weren’t included in the applicability of the existing AD. The fractured fasteners were made of A286 material, and only fasteners made of that material were installed in the diagonal brace underwing fitting. (After this, this proposed AD refers to fasteners made of A286 material as ‘‘A286 fasteners.’’) Previously, cracked or broken A286 fasteners were found only on airplanes that had a combination of alloy-steel and A286 fasteners. Thus, these previous incidents were attributed to overload of the A286 fasteners due to E:\FR\FM\01FEP1.SGM 01FEP1 5067 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules fracture of adjacent alloy-steel bolts. Fractured alloy-steel or A286 fasteners could lead to loss of the underwing fitting load path, which could result in separation of the engine and strut from the airplane. Alloy-steel or A286 fasteners may be installed in the diagonal brace underwing fitting on certain Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP series airplanes. Therefore, all of these models and series may be subject to the unsafe condition revealed on the Boeing Model 747–200B series airplanes. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. The service bulletin describes procedures for performing the following actions for the fasteners in the diagonal brace underwing fittings: • A general visual inspection to ensure that all fasteners are installed and unbroken. • A magnetic inspection to determine fastener material. • If any alloy-steel or A286 fastener is found, repetitive ultrasonic inspections for damage of all 10 aft fasteners (regardless of material). • Replacement of damaged fasteners with new, improved fasteners (including an open-hole eddy current inspection for cracking of the fastener holes, and repair if necessary). • Replacement of all alloy steel and A286 fasteners with new, improved fasteners (including an open-hole eddy current inspection for cracking of the fastener holes, and repair if necessary), which eliminates the need for the repetitive inspections. If any damage is found that exceeds certain limits, the service bulletin recommends contacting Boeing for appropriate action. Accomplishing the actions specified in the service information is intended to 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 products of this same type design. This proposed AD would supersede AD 2001–13–06. This proposed AD would retain the requirements of the existing AD. This VerDate jul<14>2003 14:57 Jan 31, 2005 Jkt 205001 proposed AD would also expand the applicability of the existing AD and require accomplishing the actions specified in the service bulletin described previously, except as discussed under ‘‘Differences Between the Proposed AD and Service Bulletin.’’ Differences Between the Proposed AD and Service Bulletin The service bulletin specifies a magnetic inspection to detect alloy-steel fasteners. We find that a detailed inspection is also necessary to detect A286 fasteners. For the purposes of this AD, an A286 fastener is any fastener to which the magnet is not attracted, and which cannot be conclusively determined to have a part number that begins with BACB30NX (fasteners of T1 material) or BACB30US (fasteners of Inconel material). This difference has been coordinated with the airplane manufacturer, and it agrees with our determination. If Boeing Alert Service Bulletin 747–57A2312 is revised in the future, the new revision will take into account the proposed requirements of this AD. If any A286 fastener is found during the inspection to determine material type, the service bulletin specifies that you must do an ultrasonic inspection for damage of all 10 aft fasteners in the diagonal brace underwing fitting. However, this proposed AD would require you to perform an ultrasonic inspection for damage of only alloy-steel and A286 fasteners, unless a cracked (or otherwise damaged) fastener is found. If a cracked or otherwise damaged fastener is found, this proposed AD would require ultrasonic inspection for damage of all 10 aft fasteners. This difference has been coordinated with the airplane manufacturer, and it agrees with our determination. If Boeing Alert Service Bulletin 747–57A2312 is revised in the future, the new revision will take into account the proposed requirements of this AD. Figure 1 of the service bulletin recommends that you perform a general visual inspection to ensure that all fasteners are installed and unbroken. We have determined that the procedures needed for this inspection constitute a detailed inspection. Note 1 of this AD defines a detailed inspection. This difference has been coordinated with the airplane manufacturer, and it agrees with our determination. If Boeing Alert Service Bulletin 747–57A2312 is revised in the future, the new revision will take into account the proposed requirements of this AD. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Section 1.E., Table 1, of the service bulletin specifies an initial inspection threshold of between 11,000 and 29,000 total flight cycles for the inspection to detect A286 fasteners. Section 1.E. of the service bulletin also specifies a grace period of 18 months after the issue date of Revision 1 of the service bulletin. This proposed AD would require compliance prior to the threshold specified in the service bulletin, or within 18 months after the effective date of the AD, whichever occurs later. The service bulletin specifies that you may contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require you to repair those conditions in one of the following ways: • Using a method that the Manager of the Seattle Aircraft Certification Office approves; or • Using data that meet the certification basis of the airplane that have been approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the FAA to make those findings. Changes to Existing AD This proposed AD would retain all requirements of AD 2001–13–06. Since AD 2001–13–06 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2001–13–06 Paragraph Paragraph Paragraph Paragraph (a) (b) (c) (d) ............ ............ ............ ............ Corresponding requirement in this proposed AD Paragraph Paragraph Paragraph Paragraph (f). (g). (l). (n). Also, we have changed all references to a ‘‘detailed visual inspection’’ in the existing AD to ‘‘detailed inspection’’ in this action. Note 1 defines a ‘‘detailed inspection.’’ Costs of Compliance There are about 739 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this proposed AD, at an average labor rate of $65 per work hour. E:\FR\FM\01FEP1.SGM 01FEP1 5068 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules ESTIMATED COSTS Action Work hours Detailed and magnetic inspection (required by AD 2001–13–06). Detailed and magnetic inspections (new proposed action). Parts Cost per airplane Number of U.S.-registered airplanes Fleet cost 2 None ........................ $130 60 $7,800 3 None ........................ 195 140 27,300 Authority for This Rulemaking The Proposed Amendment Requirements of AD 2001–13–06: 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, the FAA is charged 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 AD. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Repetitive Inspections (f) For Boeing Model 747–100, 747–200, 747–300, and 747SP series airplanes equipped with titanium diagonal brace underwing fittings, as identified in Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000: Within 12 months after August 1, 2001 (the effective date of AD 2001–13–06, amendment 39–12286), do a one-time detailed inspection of the diagonal brace underwing fitting at the Number 1 and Number 4 engine pylons to find missing taperlock fasteners (bolts), and a magnetic inspection to find alloy-steel fasteners per Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000, or Revision 1, dated April 29, 2004. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ (1) If no alloy-steel fasteners are found and no fasteners are missing, no further action is required by this paragraph. (2) If any alloy-steel fasteners are found or any fasteners are missing, before further flight, do an ultrasonic inspection of the alloy-steel fasteners to find damage per Part 2 of the Accomplishment Instructions of the service bulletin. (i) If no damaged alloy-steel fasteners are found, and no fasteners are missing: Repeat the ultrasonic inspection thereafter at intervals not to exceed 18 months until accomplishment of the terminating action required by paragraph (g) of this AD. (ii) If any damaged alloy-steel fasteners are found, or any fasteners are missing: Before further flight, do an ultrasonic inspection of all 10 aft fasteners (including non-alloy steel) per Part 2 of the Accomplishment Instructions of the service bulletin. Before further flight, replace damaged and missing fasteners with new fasteners per Part 3 of the Accomplishment Instructions of the service bulletin, except as provided by paragraph (l) of this AD. Thereafter, repeat the inspection of the remaining alloy-steel fasteners at intervals not to exceed 18 months until accomplishment of the terminating action required by paragraph (g) or the optional terminating action specified in paragraph (m) of this 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. VerDate jul<14>2003 14:57 Jan 31, 2005 Jkt 205001 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing amendment 39–12286 (66 FR 34094, June 27, 2001) and adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–20243; Directorate Identifier 2004–NM–153–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this airworthiness directive (AD) action by March 18, 2005. Affected ADs (b) This AD supersedes AD 2001–13–06, amendment 39–12286 (66 FR 34094, June 27, 2001). Applicability: (c) This AD applies to Model 747–100, 747–100B, 747–100B SUD, –200B, 747–200C, 747–200F, 747–300, 747 –400, 747–400D, 747–400F, 747SR, and 747SP series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. Unsafe Condition (d) This AD was prompted by reports indicating that cracked fasteners made of A286 material were found on airplanes that had only fasteners made of A286 material installed in the area common to the diagonal brace underwing fittings. We are issuing this AD to prevent loss of the underwing fitting load path due to missing or damaged alloysteel or A286 taperlock fasteners, which could result in separation of the engine and strut 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. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\01FEP1.SGM 01FEP1 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules Terminating Action (g) For Boeing Model 747–100, 747–200, 747–300, and 747SP series airplanes equipped with titanium diagonal brace underwing fittings, as identified in Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000: Within 48 months after August 1, 2001, do the actions required by paragraphs (g)(1) and (g)(2), or (g)(3) of this AD, per Boeing Alert Service Bulletin 747– 57A2312, dated June 15, 2000, or Revision 1, dated April 29, 2004. Accomplishment of the actions specified in this paragraph constitutes terminating action for the repetitive inspection requirements of this AD. (1) Perform an open-hole high frequency eddy current (HFEC) inspection to detect cracks, corrosion, or damage at the bolt hole locations of the aft 10 taperlock fasteners in the diagonal brace underwing fitting at the Number 1 and Number 4 engine pylons per Part 3 of the Accomplishment Instructions of the service bulletin. If any cracking is detected, before further flight, perform applicable corrective actions per the service bulletin, except as provided by paragraph (l) of this AD. (2) Before further flight: Replace all 10 aft taperlock fasteners with new, improved fasteners per Part 3 of the Accomplishment Instructions of the service bulletin. (3) Do an ultrasonic inspection to find damaged fasteners per Part 2 of the Accomplishment Instructions of the service bulletin. Before further flight, replace all damaged non-alloy steel and all alloy-steel fasteners with new fasteners per Part 3 of the Accomplishment Instructions of the service bulletin. Do an open-hole HFEC inspection before installation of the new fasteners; if any cracking, corrosion, or damage is found, before further flight, perform applicable corrective actions per the service bulletin, except as provided by paragraph (l) of this AD. New Requirements of This AD: Inspection for Missing/Broken Fasteners and To Determine Material Type (h) For all fasteners in the diagonal brace underwing fitting at the Number 1 and Number 4 engine pylons: Perform the inspections in paragraphs (h)(1) and (h)(2) of this AD, as applicable. (1) For airplanes not identified in paragraph (f) of this AD: Within 12 months after the effective date of this AD, perform a detailed inspection to ensure that all fasteners are installed and unbroken, and a magnetic inspection to detect alloy-steel fasteners, in accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. (2) For all airplanes: Before the initial inspection threshold specified in Section 1.E., Table 1, of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004; or within 18 months after the effective date of this AD; whichever is later; perform detailed and magnetic inspections, as applicable, to detect A286 fasteners in the diagonal brace underwing fitting at the Number 1 and Number 4 engine pylons, as VerDate jul<14>2003 14:57 Jan 31, 2005 Jkt 205001 specified in Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. For the purposes of this AD, an A286 fastener is any fastener to which the magnet is not attracted, and which cannot be conclusively determined to be BACB30NX (T1 material) or BACB30US (Inconel material) fasteners. Ultrasonic Inspection for Damage (i) For all alloy-steel or A286 fasteners identified during the inspections in accordance with paragraph (h) of this AD: Before further flight, perform an ultrasonic inspection for damage (including, but not limited to, cracking or corrosion) of each alloy-steel and A286 fastener, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. If any bolt is missing or found damaged during the inspection required by this paragraph: before further flight, perform an ultrasonic inspection for damage of all 10 subject fasteners, in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Doing the actions required by this paragraph within the compliance time specified in paragraph (f) of this AD eliminates the need to do paragraph (f) of this AD. Undamaged Fastener: Repetitive Inspections or No Further Action (j) For any fastener that is found to be installed and undamaged during the inspections required by paragraph (i) of this AD, do paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. (1) If no damage is found during the inspections required by paragraph (i) of this AD, and all 10 fasteners in the diagonal brace underwing fitting at the Number 1 and Number 4 engine pylons are either BACB30NX or BACB30US fasteners: No further action is required by this AD, though the restrictions of paragraph (n) of this AD, ‘‘Parts Installation,’’ apply. (2) For any undamaged alloy steel fastener: Repeat the ultrasonic inspection specified in paragraph (i) of this AD at intervals not to exceed 18 months, until the actions in paragraph (m) of this AD are done. (3) For any undamaged A286 fastener: Repeat the ultrasonic inspection specified in paragraph (i) of this AD at intervals not to exceed 8,000 flight cycles, until the actions in paragraph (m) of this AD are done. Repetitive Ultrasonic Inspections and Corrective Actions (k) For any missing or damaged fastener found during the inspections required by paragraph (i) or (j) of this AD: Before further flight, install a new, improved fastener in any location where a fastener is missing, and replace any damaged fastener with a new, improved fastener, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004. Do an openhole HFEC inspection for cracking, corrosion, or damage before installing the new fastener. If any cracking, corrosion, or damage is found: Before further flight, perform applicable corrective actions in accordance PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 5069 with the service bulletin, except as provided by paragraph (l) of this AD. Repair (l) If any damage (including but not limited to cracking or corrosion) of the bolt hole that exceeds the limits specified in Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004, is found during any inspection required by this AD, and the service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair per a method approved by the Manager, Seattle ACO, or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who the Manager, Seattle ACO, has authorized to make this finding. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically reference this AD. Optional Terminating Action (m) Replacement of all alloy steel and A286 fasteners with new, improved fasteners in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–57A2312, Revision 1, dated April 29, 2004 (including performing an open-hole eddy current inspection for cracking of the fastener holes and repairing, as applicable), constitutes terminating action for the repetitive inspection requirements of this AD. Parts Installation (n) For Boeing Model 747–100, 747–200, 747–300, and 747SP series airplanes equipped with titanium diagonal brace underwing fittings, as identified in Boeing Alert Service Bulletin 747–57A2312, dated June 15, 2000: As of August 1, 2001, no person may install, on any airplane, a fastener having part number BACB30PE( ) * ( ); or any other fastener made of 4340, 8740, PH13–8 Mo, or H–11 steel; in the locations specified in this AD. (o) Except as provided by paragraph (n) of this AD, as of the effective date of this AD no person may install, on any airplane, a fastener having part number BACB30PE( ) * ( ); or any other fastener made of 4340, 8740, PH13–8 Mo, A286, or H–11 steel; in the locations specified in this AD. Alternative Methods of Compliance (AMOCs) (p)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. (3) AMOCs approved previously according to AD 2001–13–06, amendment 39–12286 (66 E:\FR\FM\01FEP1.SGM 01FEP1 5070 Federal Register / Vol. 70, No. 20 / Tuesday, February 1, 2005 / Proposed Rules 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. Issued in Renton, Washington, on January 21, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–1794 Filed 1–31–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2000–NM–120–AD] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–120 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking; reopening of comment period. AGENCY: This document revises an earlier proposed airworthiness directive (AD), applicable to certain EMBRAER Model EMB–120 series airplanes that would have required initial and repetitive calibration testing of potentiometers to detect noisy signals and replacement of only those with noisy signals. This new action revises the proposed AD by reducing the compliance time for the repetitive calibration testing of the potentiometers and adding the requirement for reporting results of the calibration tests of the potentiometers and the readouts of the flight data recorder (FDR) to the airplane manufacturer. The actions specified by this new proposed AD are intended to prevent the potentiometers that provide information on the positions of the primary flight controls to the FDR from transmitting noisy signals or becoming improperly calibrated, resulting in the transmission of incomplete or inaccurate data to the FDR. This lack of reliable data could hamper discovery of the unsafe condition that caused an accident or incident and prevent the FAA from developing and mandating actions to prevent additional accidents or incidents caused by that same unsafe condition. This action is intended to address the identified unsafe condition. SUMMARY: VerDate jul<14>2003 14:57 Jan 31, 2005 Jkt 205001 Comments must be received by February 28, 2005. ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM–114, Attention: Rules Docket No. 2000–NM– 120–AD, 1601 Lind Avenue, SW., Renton, Washington 98055–4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to (425) 227–1232. Comments may also be sent via the Internet using the following address: 9-anmnprmcomment@faa.gov. Comments sent via fax or the Internet must contain ‘‘Docket No. 2000–NM–120–AD’’ in the subject line and need not be submitted in triplicate. Comments sent via the Internet as attached electronic files must be formatted in Microsoft Word 97 or 2000 or ASCII text. The service information referenced in the proposed rule may be obtained from Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343–CEP 12.225, Sao Jose dos Campos–SP, Brazil. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, 1601 Lind Avenue, S.W., Renton, Washington, 98055–4056; telephone (425) 227–1175; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Comments Invited Interested persons are invited to participate in the making of the proposed rule by submitting such written data, views, or arguments, as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified above. All communications received on or before the closing date for comments, specified above, will be considered before taking action on the proposed rule. The proposals contained in this action may be changed in light of the comments received. Submit comments using the following format: • Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues. • For each issue, state what specific change to the proposed AD is being requested. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 • Include justification (e.g., reasons or data) for each request. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the proposed rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report summarizing each FAA-public contact concerned with the substance of this proposal will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to Docket Number 2000–NM–120–AD.’’ The postcard will be date stamped and returned to the commenter. Availability of NPRMs Any person may obtain a copy of this NPRM by submitting a request to the FAA, Transport Airplane Directorate, ANM–114, Attention: Rules Docket No. 2000–NM–120–AD, 1601 Lind Avenue, SW., Renton, Washington 98055–4056. Discussion A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to add an airworthiness directive (AD), applicable to certain EMBRAER Model EMB–120 series airplanes, was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on March 19, 2003 (68 FR 13239), hereafter referred to as the ‘‘first supplemental NPRM.’’ That supplemental NPRM would have required initial and repetitive calibration testing of the potentiometers to detect noisy signals and replacement of only those with noisy signals. Potentiometers that provide information on the positions of the primary flight controls to the flight data recorder (FDR) transmitting noisy signals or becoming improperly calibrated, if not corrected, could result in the transmission of incomplete or inaccurate data to the FDR. This lack of reliable data could hamper discovery of the unsafe condition that caused an accident or incident and prevent the FAA from developing and mandating actions to prevent additional accidents or incidents caused by that same unsafe condition. E:\FR\FM\01FEP1.SGM 01FEP1

Agencies

[Federal Register Volume 70, Number 20 (Tuesday, February 1, 2005)]
[Proposed Rules]
[Pages 5066-5070]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-1794]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20243; Directorate Identifier 2004-NM-153-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Boeing Model 747-100, -200, -
300, and 747SP series airplanes. The existing AD currently requires 
certain inspections to find missing or alloy-steel taperlock fasteners 
(bolts) in the diagonal brace underwing fittings, and corrective 
actions if necessary. For airplanes with missing or alloy-steel 
fasteners, the existing AD also mandates replacement of certain 
fasteners with new fasteners, which constitutes terminating action for 
certain inspections. This proposed AD would expand the applicability to 
include additional airplane models and would require a new inspection 
to determine fastener material and to find missing or broken fasteners, 
and related investigative/corrective actions if necessary. This 
proposed AD is prompted by reports indicating that cracked fasteners 
made of A286 material were found on airplanes that had only fasteners 
made of A286 material installed in the area common to the diagonal 
brace underwing fittings. We are proposing this AD to prevent loss of 
the underwing fitting load path due to missing or damaged alloy-steel 
or A286 taperlock fasteners, which could result in separation of the 
engine and strut from the airplane.

DATES: We must receive comments on this proposed AD by March 18, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web Site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide Rulemaking Web Site: Go to http://
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.
     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, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person 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-2005-20243; the directorate identifier for this docket is 
2004-NM-153-AD.

FOR FURTHER INFORMATION CONTACT: Nicholas Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20243; 
Directorate Identifier 2004-NM-153-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 http://
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 our 
docket 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 the DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit http://dms.dot.gov.

Examining the Docket

    You can examine the AD docket on the Internet at http://
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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the DMS receives them.

Discussion

    On June 19, 2001, we issued AD 2001-13-06, amendment 39-12286 (66 
FR 34094, June 27, 2001), for certain Boeing Model 747-100, -200, -300, 
and 747SP series airplanes. That AD requires certain inspections to 
find missing or alloy-steel taperlock fasteners (bolts) in the diagonal 
brace underwing fittings; and corrective actions, if necessary. For 
airplanes with missing or alloy-steel fasteners, that AD also mandates 
replacement of certain fasteners with new fasteners, which constitutes 
terminating action for the repetitive inspection. That AD was prompted 
by a report indicating that broken taperlock fasteners (bolts) were 
found on the diagonal brace underwing fittings on the outboard strut at 
the Number 1 and Number 4 engine pylons on a Boeing Model 747-200 
series airplane having titanium underwing fittings. We issued that AD 
to prevent loss of the underwing fitting load path due to missing or 
damaged alloy-steel taperlock fasteners, which could result in 
separation of the engine and strut from the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2001-13-06, we have received reports indicating 
that fractured fasteners have been found on Model 747-200B series 
airplanes that weren't included in the applicability of the existing 
AD. The fractured fasteners were made of A286 material, and only 
fasteners made of that material were installed in the diagonal brace 
underwing fitting. (After this, this proposed AD refers to fasteners 
made of A286 material as ``A286 fasteners.'') Previously, cracked or 
broken A286 fasteners were found only on airplanes that had a 
combination of alloy-steel and A286 fasteners. Thus, these previous 
incidents were attributed to overload of the A286 fasteners due to

[[Page 5067]]

fracture of adjacent alloy-steel bolts. Fractured alloy-steel or A286 
fasteners could lead to loss of the underwing fitting load path, which 
could result in separation of the engine and strut from the airplane.
    Alloy-steel or A286 fasteners may be installed in the diagonal 
brace underwing fitting on certain Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes. Therefore, all of these 
models and series may be subject to the unsafe condition revealed on 
the Boeing Model 747-200B series airplanes.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-57A2312, 
Revision 1, dated April 29, 2004. The service bulletin describes 
procedures for performing the following actions for the fasteners in 
the diagonal brace underwing fittings:
     A general visual inspection to ensure that all fasteners 
are installed and unbroken.
     A magnetic inspection to determine fastener material.
     If any alloy-steel or A286 fastener is found, repetitive 
ultrasonic inspections for damage of all 10 aft fasteners (regardless 
of material).
     Replacement of damaged fasteners with new, improved 
fasteners (including an open-hole eddy current inspection for cracking 
of the fastener holes, and repair if necessary).
     Replacement of all alloy steel and A286 fasteners with 
new, improved fasteners (including an open-hole eddy current inspection 
for cracking of the fastener holes, and repair if necessary), which 
eliminates the need for the repetitive inspections.
    If any damage is found that exceeds certain limits, the service 
bulletin recommends contacting Boeing for appropriate action.
    Accomplishing the actions specified in the service information is 
intended to 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 products 
of this same type design. This proposed AD would supersede AD 2001-13-
06. This proposed AD would retain the requirements of the existing AD. 
This proposed AD would also expand the applicability of the existing AD 
and require accomplishing the actions specified in the service bulletin 
described previously, except as discussed under ``Differences Between 
the Proposed AD and Service Bulletin.''

Differences Between the Proposed AD and Service Bulletin

    The service bulletin specifies a magnetic inspection to detect 
alloy-steel fasteners. We find that a detailed inspection is also 
necessary to detect A286 fasteners. For the purposes of this AD, an 
A286 fastener is any fastener to which the magnet is not attracted, and 
which cannot be conclusively determined to have a part number that 
begins with BACB30NX (fasteners of T1 material) or BACB30US (fasteners 
of Inconel material). This difference has been coordinated with the 
airplane manufacturer, and it agrees with our determination. If Boeing 
Alert Service Bulletin 747-57A2312 is revised in the future, the new 
revision will take into account the proposed requirements of this AD.
    If any A286 fastener is found during the inspection to determine 
material type, the service bulletin specifies that you must do an 
ultrasonic inspection for damage of all 10 aft fasteners in the 
diagonal brace underwing fitting. However, this proposed AD would 
require you to perform an ultrasonic inspection for damage of only 
alloy-steel and A286 fasteners, unless a cracked (or otherwise damaged) 
fastener is found. If a cracked or otherwise damaged fastener is found, 
this proposed AD would require ultrasonic inspection for damage of all 
10 aft fasteners. This difference has been coordinated with the 
airplane manufacturer, and it agrees with our determination. If Boeing 
Alert Service Bulletin 747-57A2312 is revised in the future, the new 
revision will take into account the proposed requirements of this AD.
    Figure 1 of the service bulletin recommends that you perform a 
general visual inspection to ensure that all fasteners are installed 
and unbroken. We have determined that the procedures needed for this 
inspection constitute a detailed inspection. Note 1 of this AD defines 
a detailed inspection. This difference has been coordinated with the 
airplane manufacturer, and it agrees with our determination. If Boeing 
Alert Service Bulletin 747-57A2312 is revised in the future, the new 
revision will take into account the proposed requirements of this AD.
    Section 1.E., Table 1, of the service bulletin specifies an initial 
inspection threshold of between 11,000 and 29,000 total flight cycles 
for the inspection to detect A286 fasteners. Section 1.E. of the 
service bulletin also specifies a grace period of 18 months after the 
issue date of Revision 1 of the service bulletin. This proposed AD 
would require compliance prior to the threshold specified in the 
service bulletin, or within 18 months after the effective date of the 
AD, whichever occurs later.
    The service bulletin specifies that you may contact the 
manufacturer for instructions on how to repair certain conditions, but 
this proposed AD would require you to repair those conditions in one of 
the following ways:
     Using a method that the Manager of the Seattle Aircraft 
Certification Office approves; or
     Using data that meet the certification basis of the 
airplane that have been approved by an Authorized Representative for 
the Boeing Delegation Option Authorization Organization who has been 
authorized by the FAA to make those findings.

Changes to Existing AD

    This proposed AD would retain all requirements of AD 2001-13-06. 
Since AD 2001-13-06 was issued, the AD format has been revised, and 
certain paragraphs have been rearranged. As a result, the corresponding 
paragraph identifiers have changed in this proposed AD, as listed in 
the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
                                             Corresponding  requirement
       Requirement in AD 2001-13-06              in this proposed AD
------------------------------------------------------------------------
Paragraph (a).............................  Paragraph (f).
Paragraph (b).............................  Paragraph (g).
Paragraph (c).............................  Paragraph (l).
Paragraph (d).............................  Paragraph (n).
------------------------------------------------------------------------

    Also, we have changed all references to a ``detailed visual 
inspection'' in the existing AD to ``detailed inspection'' in this 
action. Note 1 defines a ``detailed inspection.''

Costs of Compliance

    There are about 739 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD, at an average labor 
rate of $65 per work hour.

[[Page 5068]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of U.S.-
            Action                Work hours          Parts          Cost per       registered      Fleet cost
                                                                     airplane        airplanes
----------------------------------------------------------------------------------------------------------------
Detailed and magnetic                        2  None............            $130              60          $7,800
 inspection (required by AD
 2001-13-06).
Detailed and magnetic                        3  None............             195             140          27,300
 inspections (new proposed
 action).
----------------------------------------------------------------------------------------------------------------

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, the FAA is charged 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 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 removing amendment 39-12286 (66 FR 
34094, June 27, 2001) and adding the following new airworthiness 
directive (AD):

Boeing: Docket No. FAA-2005-20243; Directorate Identifier 2004-NM-
153-AD.

Comments Due Date

    (a) The Federal Aviation Administration must receive comments on 
this airworthiness directive (AD) action by March 18, 2005.

Affected ADs

    (b) This AD supersedes AD 2001-13-06, amendment 39-12286 (66 FR 
34094, June 27, 2001).

Applicability:

    (c) This AD applies to Model 747-100, 747-100B, 747-100B SUD, -
200B, 747-200C, 747-200F, 747-300, 747 -400, 747-400D, 747-400F, 
747SR, and 747SP series airplanes; certificated in any category; as 
identified in Boeing Alert Service Bulletin 747-57A2312, Revision 1, 
dated April 29, 2004.

Unsafe Condition

    (d) This AD was prompted by reports indicating that cracked 
fasteners made of A286 material were found on airplanes that had 
only fasteners made of A286 material installed in the area common to 
the diagonal brace underwing fittings. We are issuing this AD to 
prevent loss of the underwing fitting load path due to missing or 
damaged alloy-steel or A286 taperlock fasteners, which could result 
in separation of the engine and strut 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.

Requirements of AD 2001-13-06:

Repetitive Inspections

    (f) For Boeing Model 747-100, 747-200, 747-300, and 747SP series 
airplanes equipped with titanium diagonal brace underwing fittings, 
as identified in Boeing Alert Service Bulletin 747-57A2312, dated 
June 15, 2000: Within 12 months after August 1, 2001 (the effective 
date of AD 2001-13-06, amendment 39-12286), do a one-time detailed 
inspection of the diagonal brace underwing fitting at the Number 1 
and Number 4 engine pylons to find missing taperlock fasteners 
(bolts), and a magnetic inspection to find alloy-steel fasteners per 
Part 1 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-57A2312, dated June 15, 2000, or Revision 1, dated 
April 29, 2004.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

    (1) If no alloy-steel fasteners are found and no fasteners are 
missing, no further action is required by this paragraph.
    (2) If any alloy-steel fasteners are found or any fasteners are 
missing, before further flight, do an ultrasonic inspection of the 
alloy-steel fasteners to find damage per Part 2 of the 
Accomplishment Instructions of the service bulletin.
    (i) If no damaged alloy-steel fasteners are found, and no 
fasteners are missing: Repeat the ultrasonic inspection thereafter 
at intervals not to exceed 18 months until accomplishment of the 
terminating action required by paragraph (g) of this AD.
    (ii) If any damaged alloy-steel fasteners are found, or any 
fasteners are missing: Before further flight, do an ultrasonic 
inspection of all 10 aft fasteners (including non-alloy steel) per 
Part 2 of the Accomplishment Instructions of the service bulletin. 
Before further flight, replace damaged and missing fasteners with 
new fasteners per Part 3 of the Accomplishment Instructions of the 
service bulletin, except as provided by paragraph (l) of this AD. 
Thereafter, repeat the inspection of the remaining alloy-steel 
fasteners at intervals not to exceed 18 months until accomplishment 
of the terminating action required by paragraph (g) or the optional 
terminating action specified in paragraph (m) of this AD.

[[Page 5069]]

Terminating Action

    (g) For Boeing Model 747-100, 747-200, 747-300, and 747SP series 
airplanes equipped with titanium diagonal brace underwing fittings, 
as identified in Boeing Alert Service Bulletin 747-57A2312, dated 
June 15, 2000: Within 48 months after August 1, 2001, do the actions 
required by paragraphs (g)(1) and (g)(2), or (g)(3) of this AD, per 
Boeing Alert Service Bulletin 747-57A2312, dated June 15, 2000, or 
Revision 1, dated April 29, 2004. Accomplishment of the actions 
specified in this paragraph constitutes terminating action for the 
repetitive inspection requirements of this AD.
    (1) Perform an open-hole high frequency eddy current (HFEC) 
inspection to detect cracks, corrosion, or damage at the bolt hole 
locations of the aft 10 taperlock fasteners in the diagonal brace 
underwing fitting at the Number 1 and Number 4 engine pylons per 
Part 3 of the Accomplishment Instructions of the service bulletin. 
If any cracking is detected, before further flight, perform 
applicable corrective actions per the service bulletin, except as 
provided by paragraph (l) of this AD.
    (2) Before further flight: Replace all 10 aft taperlock 
fasteners with new, improved fasteners per Part 3 of the 
Accomplishment Instructions of the service bulletin.
    (3) Do an ultrasonic inspection to find damaged fasteners per 
Part 2 of the Accomplishment Instructions of the service bulletin. 
Before further flight, replace all damaged non-alloy steel and all 
alloy-steel fasteners with new fasteners per Part 3 of the 
Accomplishment Instructions of the service bulletin. Do an open-hole 
HFEC inspection before installation of the new fasteners; if any 
cracking, corrosion, or damage is found, before further flight, 
perform applicable corrective actions per the service bulletin, 
except as provided by paragraph (l) of this AD.

New Requirements of This AD:

Inspection for Missing/Broken Fasteners and To Determine Material Type

    (h) For all fasteners in the diagonal brace underwing fitting at 
the Number 1 and Number 4 engine pylons: Perform the inspections in 
paragraphs (h)(1) and (h)(2) of this AD, as applicable.
    (1) For airplanes not identified in paragraph (f) of this AD: 
Within 12 months after the effective date of this AD, perform a 
detailed inspection to ensure that all fasteners are installed and 
unbroken, and a magnetic inspection to detect alloy-steel fasteners, 
in accordance with Part 1 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April 
29, 2004.
    (2) For all airplanes: Before the initial inspection threshold 
specified in Section 1.E., Table 1, of Boeing Alert Service Bulletin 
747-57A2312, Revision 1, dated April 29, 2004; or within 18 months 
after the effective date of this AD; whichever is later; perform 
detailed and magnetic inspections, as applicable, to detect A286 
fasteners in the diagonal brace underwing fitting at the Number 1 
and Number 4 engine pylons, as specified in Part 1 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. For the purposes of this 
AD, an A286 fastener is any fastener to which the magnet is not 
attracted, and which cannot be conclusively determined to be 
BACB30NX (T1 material) or BACB30US (Inconel material) fasteners.

Ultrasonic Inspection for Damage

    (i) For all alloy-steel or A286 fasteners identified during the 
inspections in accordance with paragraph (h) of this AD: Before 
further flight, perform an ultrasonic inspection for damage 
(including, but not limited to, cracking or corrosion) of each 
alloy-steel and A286 fastener, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. If any bolt is missing or 
found damaged during the inspection required by this paragraph: 
before further flight, perform an ultrasonic inspection for damage 
of all 10 subject fasteners, in accordance with Part 2 of the 
Accomplishment Instructions of the service bulletin. Doing the 
actions required by this paragraph within the compliance time 
specified in paragraph (f) of this AD eliminates the need to do 
paragraph (f) of this AD.

Undamaged Fastener: Repetitive Inspections or No Further Action

    (j) For any fastener that is found to be installed and undamaged 
during the inspections required by paragraph (i) of this AD, do 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable.
    (1) If no damage is found during the inspections required by 
paragraph (i) of this AD, and all 10 fasteners in the diagonal brace 
underwing fitting at the Number 1 and Number 4 engine pylons are 
either BACB30NX or BACB30US fasteners: No further action is required 
by this AD, though the restrictions of paragraph (n) of this AD, 
``Parts Installation,'' apply.
    (2) For any undamaged alloy steel fastener: Repeat the 
ultrasonic inspection specified in paragraph (i) of this AD at 
intervals not to exceed 18 months, until the actions in paragraph 
(m) of this AD are done.
    (3) For any undamaged A286 fastener: Repeat the ultrasonic 
inspection specified in paragraph (i) of this AD at intervals not to 
exceed 8,000 flight cycles, until the actions in paragraph (m) of 
this AD are done.

Repetitive Ultrasonic Inspections and Corrective Actions

    (k) For any missing or damaged fastener found during the 
inspections required by paragraph (i) or (j) of this AD: Before 
further flight, install a new, improved fastener in any location 
where a fastener is missing, and replace any damaged fastener with a 
new, improved fastener, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
57A2312, Revision 1, dated April 29, 2004. Do an open-hole HFEC 
inspection for cracking, corrosion, or damage before installing the 
new fastener. If any cracking, corrosion, or damage is found: Before 
further flight, perform applicable corrective actions in accordance 
with the service bulletin, except as provided by paragraph (l) of 
this AD.

Repair

    (l) If any damage (including but not limited to cracking or 
corrosion) of the bolt hole that exceeds the limits specified in 
Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April 
29, 2004, is found during any inspection required by this AD, and 
the service bulletin specifies to contact Boeing for appropriate 
action: Before further flight, repair per a method approved by the 
Manager, Seattle ACO, or according to data meeting the certification 
basis of the airplane approved by an Authorized Representative for 
the Boeing Delegation Option Authorization Organization who the 
Manager, Seattle ACO, has authorized to make this finding. For a 
repair method to be approved by the Manager, Seattle ACO, as 
required by this paragraph, the Manager's approval letter must 
specifically reference this AD.

Optional Terminating Action

    (m) Replacement of all alloy steel and A286 fasteners with new, 
improved fasteners in accordance with Part 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-57A2312, Revision 
1, dated April 29, 2004 (including performing an open-hole eddy 
current inspection for cracking of the fastener holes and repairing, 
as applicable), constitutes terminating action for the repetitive 
inspection requirements of this AD.

Parts Installation

    (n) For Boeing Model 747-100, 747-200, 747-300, and 747SP series 
airplanes equipped with titanium diagonal brace underwing fittings, 
as identified in Boeing Alert Service Bulletin 747-57A2312, dated 
June 15, 2000: As of August 1, 2001, no person may install, on any 
airplane, a fastener having part number BACB30PE( ) * ( ); or any 
other fastener made of 4340, 8740, PH13-8 Mo, or H-11 steel; in the 
locations specified in this AD.
    (o) Except as provided by paragraph (n) of this AD, as of the 
effective date of this AD no person may install, on any airplane, a 
fastener having part number BACB30PE( ) * ( ); or any other fastener 
made of 4340, 8740, PH13-8 Mo, A286, or H-11 steel; in the locations 
specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (p)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Delegation Option 
Authorization Organization who has been authorized by the Manager, 
Seattle ACO, to make those findings. For a repair method to be 
approved, the repair must meet the certification basis of the 
airplane and the approval must specifically refer to this AD.
    (3) AMOCs approved previously according to AD 2001-13-06, 
amendment 39-12286 (66

[[Page 5070]]

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.

    Issued in Renton, Washington, on January 21, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-1794 Filed 1-31-05; 8:45 am]
BILLING CODE 4910-13-P