Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, and -300 Series Airplanes; and Model 747SP and 747SR Series Airplanes, 18332-18335 [05-7155]

Download as PDF 18332 Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Proposed Rules (iii) For Area 3: Before the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later. (2) For airplanes that have been inspected in accordance with the requirements of paragraph (f) or (h) of this AD, but not the requirements of paragraph (i) of this AD: (i) For Area 1: Before the accumulation of 22,000 total flight cycles, or within 3,000 flight cycles after the most recent inspection required by paragraph (f) or (h) of this AD, whichever is later. (ii) For Area 2: Before the accumulation of 28,000 total flight cycles, or within 3,000 flight cycles after the most recent inspection required by paragraph (f) or (h) of this AD, whichever is later. (iii) For Area 3: Before the accumulation of 22,000 total flight cycles, or within 3,000 flight cycles after the most recent inspection required by paragraph (f) or (h) of this AD, whichever is later. (3) For airplanes on which a surface HFEC inspection of the horizontal flanges of the upper chord of the upper deck floor beams, as required by paragraph (i) of this AD, was accomplished, and the surface HFEC inspection was accomplished from below the upper deck floor beams as specified by Figure 2, circle note 2c., of Boeing Alert Service Bulletin 747–53A2349, Revision 1: (i) For Area 1: At the later of the times specified in paragraphs (m)(3)(i)(A) and (m)(3)(i)(B) of this AD. (A) Before the accumulation of 22,000 total flight cycles. (B) Within 2,000 flight cycles after the most recent inspection required by paragraph (i) of this AD, or 750 flight cycles after the effective date of this AD, whichever is first. (ii) For Area 2: Before the accumulation of 28,000 total flight cycles, or within 2,000 flight cycles after the most recent inspection required by paragraph (i) of this AD, whichever is later. (iii) For Area 3: Before the accumulation of 22,000 total flight cycles, or within 3,000 flight cycles after the most recent inspection required by paragraph (f) or (h) of this AD, whichever is later. (4) For airplanes on which either a surface or open-hole HFEC inspection of the horizontal flanges of the upper chord of the upper deck floor beams, as required by paragraph (i) of this AD has been accomplished, and the surface HFEC inspection was accomplished from above and below the upper deck floor beams, as specified by Figure 2, circle note 2b., of Boeing Alert Service Bulletin 747–53A2349, Revision 1: (i) For Area 1: At the later of the times specified in paragraphs (m)(4)(i)(A) and (m)(4)(ii)(B) of this AD. (A) Before the accumulation of 22,000 total flight cycles. (B) Within 6,000 flight cycles after the most recent inspection required by paragraph (i) of this AD, or within 3,000 flight cycles after the effective date of this AD whichever is first. (ii) For Area 2: Before the accumulation of 28,000 total flight cycles, or within 6,000 flight cycles after the most recent inspection required by paragraph (i) of this AD, whichever is later. VerDate jul<14>2003 16:24 Apr 08, 2005 Jkt 205001 (iii) For Area 3: Before the accumulation of 22,000 total flight cycles, or within 3,000 flight cycles after the most recent inspection required by paragraph (f) or (h) of this AD, whichever is latest. Repetitive Inspections (n) Except as required by paragraphs (o), (p), and (q) of this AD, repeat the inspections required by paragraph (m) of this AD at intervals not to exceed those specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD: (1) For Area 1: 3,000 flight cycles if an open-hole HFEC inspection was accomplished, or 750 flight cycles if a surface HFEC inspection was accomplished. (2) For Area 2: 6,000 flight cycles if an open-hole HFEC inspection was accomplished, or 2,000 flight cycles if a surface HFEC inspection was accomplished. (3) For Area 3: 3,000 flight cycles. Repair (o) Before further flight, repair any cracking found during any inspection required by paragraph (l), (m), or (n) of this AD in accordance with Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003. Repairs done in accordance with the service bulletin terminates the requirements of paragraphs (l), (m), and (n) of this AD for the repaired area only. Where the service bulletin specifies to contact Boeing for repair instructions, repair according to a method approved by the Manager, Seattle ACO; or according to data meeting the certification basis of the airplane approved by an AR for the Boeing DOA 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. After-Repair Inspections (p) At the applicable new inspection thresholds specified in Figure 1 of Boeing Alert Service Bulletin 747–53A2452, dated April 3, 2003, perform the after-repair inspections for cracking in Areas 1 and 2, as specified in the service bulletin. Where the service bulletin specifies a threshold after the date of the service bulletin, use that same threshold after the effective date of this AD. Perform the after-repair inspections by accomplishing all of the applicable actions specified in the alert service bulletin. Repair any cracking found during any inspection required by this paragraph, according to a method approved by the Manager, Seattle ACO; or according to data meeting the certification basis of the airplane approved by an AR for the Boeing DOA who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the approval letter must specifically reference this AD. Any cracking found during any inspection must be repaired before further flight. Repeat the inspections of Areas 1 and 2 thereafter at intervals not to exceed 3,000 flight cycles. Optional Preventative Modification (q) If no cracking was found during the open-hole HFEC inspections required by paragraph (m) or (n) of this AD, repairing or PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 modifying Areas 1 and 2, as defined in Figure 1 of Boeing Alert Service Bulletin 747– 53A2452, dated April 3, 2003, in accordance with the service bulletin, defers the repetitive inspections required by paragraph (n) of this AD, and establishes new inspection methods, thresholds, and repetitive inspection intervals for the repaired or modified area. The new inspection thresholds and intervals are specified in Figure 1 of the service bulletin. Where the service bulletin specifies a threshold after the date of the service bulletin, use that same threshold after the effective date of this AD. Inspections Done Previously (r) Doing the inspections required by paragraphs (m) and (n) of this AD before the effective date of this AD, in accordance with the Accomplishment Instructions in Boeing Alert Service Bulletin 747–53A2349, Revision 1, dated October 12, 2000, is acceptable for compliance with the corresponding actions required by this AD. Alternative Methods of Compliance (AMOCs) (s)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Alternative methods of compliance and FAA-approved repairs, approved previously in accordance with AD 2002–10–10 are approved as AMOCs for the corresponding actions required by this AD. Issued in Renton, Washington, on April 1, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7154 Filed 4–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20880; Directorate Identifier 2003–NM–229–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, –100B, –100B SUD, –200B, and –300 Series Airplanes; and Model 747SP and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks in various areas of the fuselage E:\FR\FM\11APP1.SGM 11APP1 Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Proposed Rules internal structure, and repair if necessary. This proposed AD would require repetitive inspections of additional areas of the fuselage internal structure, and related investigative/ corrective actions if necessary. This proposed AD also would remove certain requirements from the existing AD. This proposed AD is prompted by the results of fatigue testing of the fuselage structure of a Boeing Model 747SR series airplane. We are proposing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane. DATES: We must receive comments on this proposed AD by May 26, 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. • 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 Airplane Group, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at https:// 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– 20880; the directorate identifier for this docket is 2003–NM–229–AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; 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– VerDate jul<14>2003 16:24 Apr 08, 2005 Jkt 205001 2005–20880; Directorate Identifier 2003–NM–229–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 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 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 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 On May 14, 2002, we issued AD 2002–10–10, amendment 39–12756 (67 FR 36081, May 23, 2002), for certain Boeing Model 747 series airplanes. That AD requires repetitive inspections to detect cracking in various areas of the fuselage internal structure, and repair if necessary. That AD was prompted by the results of fatigue testing that revealed severed upper chords of the upper deck floor beams due to fatigue cracking. We issued that AD to prevent loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane. Actions Since Existing AD Was Issued Since we issued AD 2002–10–10, the manufacturer reported that cracking was found on the fatigue test airplane in areas not included in Boeing Service Bulletin 747–53–2349, dated June 27, 1991; or Boeing Alert Service Bulletin 747–53A2349, Revision 1, dated PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 18333 October 12, 2000. (Those service bulletins were referenced as the appropriate sources of service information in AD 2002–10–10.) The new areas are the fuselage skin at all four corners of the main electronics bay access door cutout, and certain nose wheel well (NWW) sidewall panels and stiffeners, and certain main deck floor beams at the NWW vertical beams. Relevant Service Information We have reviewed Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. The service bulletin describes procedures that are essentially the same as the procedures in Boeing Alert Service Bulletin 747–53A2349, Revision 1. Revision 2 includes a new inspection area, Area 9. Area 9 includes the fuselage skin at all four corners of the main electronics bay access door cutout. Revision 2 also includes additional inspections in Area 7. Area 7 now includes certain NWW sidewall panels and stiffeners between STA 340 and STA 400, and the STA 360 and 380 main deck floor beams at the NWW vertical beams. The actions described in Revision 2 also affect Area 1. Among other things, for Group 3 airplanes only, Area 1 has also been redefined. For airplanes on which any cracking is found, Revision 2 references the Boeing 747 Structural Repair Manual for repair instructions. For airplanes with damage that is beyond the limits specified in the service bulletin, the service bulletin specifies contacting Boeing for repair data. 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. Therefore, we are proposing this AD, which would supersede AD 2002–10–10. This proposed AD would continue to require repetitive inspections to detect cracks in various areas of the fuselage internal structure, and repair if necessary. This proposed AD would also require repetitive inspections of additional areas of the fuselage internal structure, and related investigative/corrective actions if necessary. This proposed AD also would remove all requirements related to the upper deck floor beams from the existing AD, as discussed below under ‘‘Other Related Rulemaking.’’ This proposed AD would require you to use the service information described previously to perform these actions, except as discussed under ‘‘Differences Between E:\FR\FM\11APP1.SGM 11APP1 18334 Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Proposed Rules the Proposed AD and Service Information.’’ Other Related Rulemaking Operators should note that we plan to issue a separate AD rulemaking action (reference Directorate Identifier 2004– NM–55–AD) to address the identified unsafe condition as it relates to the upper deck floor beams. Therefore, all requirements from AD 2002–10–10 that relate to the upper deck floor beams are in that separate AD rulemaking action. Differences Between the Proposed AD and Service Information 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 we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization whom we have authorized to make those findings. proposed AD, as listed in the following table: REVISED PARAGRAPH IDENTIFIERS Requirement in AD 2002–10–10 Paragraph (a) ................. Paragraph (b) ................. Paragraph (c) ................. Corresponding requirement in this proposed AD Paragraph (f). Paragraph (g). Paragraph (h). Change to Existing AD This proposed AD would retain certain requirements of AD 2002–10–10. Since AD 2002–10–10 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 Costs of Compliance This proposed AD would affect about 489 airplanes worldwide, and 155 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. ESTIMATED COSTS Work hours Action Inspections, excluding upper deck floor beams, per inspection cycle (required by AD 2002–10–10). Inspections (new proposed AD) ........................................ Average labor rate per hour Parts None ........ $9,425 155 $1,460,875 130 65 None ........ 8,450 155 1,309,750 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: Jkt 205001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: PO 00000 Authority: 49 U.S.C. 106(g), 40113, 44701. Frm 00014 Fleet cost $65 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. 16:24 Apr 08, 2005 Number of U.S. registered airplanes 145 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. VerDate jul<14>2003 Cost per airplane, per inspection cycle Fmt 4702 Sfmt 4702 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing amendment 39–12756 (67 FR 36081, May 23, 2002) and adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–20880; Directorate Identifier 2003–NM–229–AD. Comments Due Date (a) The Federal Aviation Administration must receive comments on this airworthiness directive (AD) action by May 26, 2005. Affected ADs (b) This AD supersedes AD 2002–10–10, amendment 39–12756 (67 FR 36081, May 23, 2002). Applicability (c) This AD applies to Boeing Model 747– 100, –100B, –100B SUD, –200B, and –300 series airplanes; and Model 747SP and 747SR series airplanes; certificated in any category; identified in Boeing Service Bulletin 747– 53A2349, Revision 2, dated April 3, 2003. Unsafe Condition (d) This AD was prompted by the results of fatigue testing of the fuselage structure of a Boeing Model 747SR series airplane. We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within E:\FR\FM\11APP1.SGM 11APP1 Federal Register / Vol. 70, No. 68 / Monday, April 11, 2005 / Proposed Rules the compliance times specified, unless the actions have already been done. Restatement of Requirements of AD 2002– 10–10 (Excluding Upper Deck Floor Beams) Repetitive Inspections (f) Prior to the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after June 11, 1993 (the effective date of AD 93–08–12, amendment 39–8559), whichever occurs later, unless accomplished previously within the last 2,000 flight cycles; and thereafter at intervals not to exceed 3,000 flight cycles: Perform an internal detailed inspection to detect cracks in the areas of the fuselage internal structure specified in paragraphs (f)(1) through (f)(6) of this AD; in accordance with Boeing Service Bulletin 747–53–2349, dated June 27, 1991; Boeing Alert Service Bulletin 747–53A2349, Revision 1, dated October 12, 2000; or Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. After the effective date of this AD, only Revision 2 of Boeing Service Bulletin 747–53A2349 may be used. Continue doing the inspections until the inspections required by paragraph (i) of this AD are done. (1) Section 42 upper lobe frames. (2) Section 46 lower lobe frames. (3) Section 42 lower lobe frames. (4) Main entry door cutouts. (5) Section 41 body station 260, 340, and 400 bulkheads. (6) Main entry doors. 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.’’ (g) Prior to the accumulation of 25,000 total flight cycles, or within 1,000 flight cycles after June 11, 1993, whichever is later, unless already done within the last 2,000 flight cycles; and thereafter at intervals not to exceed 3,000 flight cycles: Do an internal detailed inspection to detect cracks in the Section 46 upper lobe frames, in accordance with Boeing Service Bulletin 747–53–2349, dated June 27, 1991; Boeing Alert Service Bulletin 747–53A2349, Revision 1, dated October 12, 2000; or Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. After the effective date of this AD, only Revision 2 of Boeing Service Bulletin 747– 53A2349 may be used. Repair (h) Before further flight, repair any cracks detected during the inspections done per paragraph (f) or (g) of this AD, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane approved a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings; or by an Authorized VerDate jul<14>2003 16:24 Apr 08, 2005 Jkt 205001 Representative (AR) for the Boeing Delegation Option Authorization (DOA) 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. New Requirements of This AD Repetitive Inspections (i) Do an internal detailed inspection to detect cracking in the areas of the fuselage internal structure specified in paragraphs (i)(1), (i)(2), (i)(3), and (i)(5) of this AD, and internal and external detailed inspections of the areas specified in paragraphs (i)(4), (i)(6), and (i)(7) of this AD. Do the inspections in accordance with Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. Do the inspections at the applicable time specified in paragraph (j) of this AD. Accomplishment of these inspections terminates the requirements of paragraph (f) of this AD. (1) Section 42 upper lobe frames. (2) Section 46 lower lobe frames. (3) Section 42 lower lobe frames. (4) Main entry door cutouts. (5) Nose wheel well bulkheads, sidewall panels, and the STA 360 and 380 floor beams. These areas include the Section 41 body station 260, 340, and 400 bulkheads. (6) Main entry doors. (7) Main electronics bay access door cutout. (j) Do the inspections required by paragraph (i) of this AD at the applicable time specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. (1) For airplanes on which the inspections required by paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6) of this AD have been done before the effective date of this AD, but the inspections required by paragraphs (i)(5) and (i)(7) of this AD have not been done: Within 3,000 flight cycles since accomplishment of the most recent inspection required by paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6) of this AD. (2) For airplanes on which the inspections required by paragraphs (i)(5) and (i)(7) have been done before the effective date of this AD: Within 3,000 flight cycles since accomplishment of the most recent inspection required by paragraphs (i)(5) and (i)(7) of this AD, or within 1,000 flight cycles after the effective date of this AD, whichever is later. (3) For airplanes on which the inspections required by paragraph (f) of this AD have not been done before the effective date of this AD: Prior to the accumulation of 22,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later. Repair (k) Before further flight, repair any cracking found during any inspection required by paragraph (i) of this AD in accordance with Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003. Where the service bulletin specifies to contact Boeing for repair instructions, repair in accordance PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 18335 with a method approved by the Manager, Seattle ACO; or in accordance with data meeting the type certification basis of the airplane, and that have been approved by an AR for the Boeing DOA who has been authorized by the FAA to make those findings. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the approval letter must specifically reference this AD. Actions Previously Accomplished (l) Inspections required by paragraph (i) of this AD, accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53–2349, dated June 27, 1991; or Boeing Alert Service Bulletin 747– 53A2349, Revision 1, dated October 12, 2000; are acceptable for compliance with the corresponding action required by paragraph (i) of this AD. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Seattle ACO, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Alternative methods of compliance and FAA-approved repairs, approved previously in accordance with AD 2002–10–10 or AD 93–08–12, are approved as alternative methods of compliance with the corresponding requirements of this AD. Issued in Renton, Washington, on April 1, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7155 Filed 4–8–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2005–20617; Airspace Docket No. 05–AAL–12] RIN 2120–AA66 Proposed Establishment of Area Navigation Routes (RNAV); Alaska Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This action proposes to establish one low altitude area navigation (RNAV) route in Alaska to support the Alaskan Capstone Program. The FAA is proposing this action to enhance safety and improve the efficient use of the navigable airspace in Alaska. DATES: Comments must be received on or before May 26, 2005. ADDRESSES: Send comments on this proposal to the Docket Management E:\FR\FM\11APP1.SGM 11APP1

Agencies

[Federal Register Volume 70, Number 68 (Monday, April 11, 2005)]
[Proposed Rules]
[Pages 18332-18335]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7155]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20880; Directorate Identifier 2003-NM-229-AD]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD,
-200B, and -300 Series Airplanes; and Model 747SP and 747SR Series
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for certain Boeing Model 747 series airplanes. That AD
currently requires repetitive inspections to detect cracks in various
areas of the fuselage

[[Page 18333]]

internal structure, and repair if necessary. This proposed AD would
require repetitive inspections of additional areas of the fuselage
internal structure, and related investigative/corrective actions if
necessary. This proposed AD also would remove certain requirements from
the existing AD. This proposed AD is prompted by the results of fatigue
testing of the fuselage structure of a Boeing Model 747SR series
airplane. We are proposing this AD to prevent the loss of the
structural integrity of the fuselage, which could result in rapid
depressurization of the airplane.

DATES: We must receive comments on this proposed AD by May 26, 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.
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 Airplane Group, P.O. Box 3707, Seattle, Washington
98124-2207.
You can examine the contents of this AD docket on the Internet at
https://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-2005-20880; the directorate identifier for this docket is
2003-NM-229-AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437;
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-2005-20880;
Directorate Identifier 2003-NM-229-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 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 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 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

On May 14, 2002, we issued AD 2002-10-10, amendment 39-12756 (67 FR
36081, May 23, 2002), for certain Boeing Model 747 series airplanes.
That AD requires repetitive inspections to detect cracking in various
areas of the fuselage internal structure, and repair if necessary. That
AD was prompted by the results of fatigue testing that revealed severed
upper chords of the upper deck floor beams due to fatigue cracking. We
issued that AD to prevent loss of the structural integrity of the
fuselage, which could result in rapid depressurization of the airplane.

Actions Since Existing AD Was Issued

Since we issued AD 2002-10-10, the manufacturer reported that
cracking was found on the fatigue test airplane in areas not included
in Boeing Service Bulletin 747-53-2349, dated June 27, 1991; or Boeing
Alert Service Bulletin 747-53A2349, Revision 1, dated October 12, 2000.
(Those service bulletins were referenced as the appropriate sources of
service information in AD 2002-10-10.) The new areas are the fuselage
skin at all four corners of the main electronics bay access door
cutout, and certain nose wheel well (NWW) sidewall panels and
stiffeners, and certain main deck floor beams at the NWW vertical
beams.

Relevant Service Information

We have reviewed Boeing Service Bulletin 747-53A2349, Revision 2,
dated April 3, 2003. The service bulletin describes procedures that are
essentially the same as the procedures in Boeing Alert Service Bulletin
747-53A2349, Revision 1. Revision 2 includes a new inspection area,
Area 9. Area 9 includes the fuselage skin at all four corners of the
main electronics bay access door cutout. Revision 2 also includes
additional inspections in Area 7. Area 7 now includes certain NWW
sidewall panels and stiffeners between STA 340 and STA 400, and the STA
360 and 380 main deck floor beams at the NWW vertical beams. The
actions described in Revision 2 also affect Area 1. Among other things,
for Group 3 airplanes only, Area 1 has also been redefined.
For airplanes on which any cracking is found, Revision 2 references
the Boeing 747 Structural Repair Manual for repair instructions. For
airplanes with damage that is beyond the limits specified in the
service bulletin, the service bulletin specifies contacting Boeing for
repair data.

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. Therefore, we are proposing this AD, which
would supersede AD 2002-10-10. This proposed AD would continue to
require repetitive inspections to detect cracks in various areas of the
fuselage internal structure, and repair if necessary. This proposed AD
would also require repetitive inspections of additional areas of the
fuselage internal structure, and related investigative/corrective
actions if necessary. This proposed AD also would remove all
requirements related to the upper deck floor beams from the existing
AD, as discussed below under ``Other Related Rulemaking.'' This
proposed AD would require you to use the service information described
previously to perform these actions, except as discussed under
``Differences Between

[[Page 18334]]

the Proposed AD and Service Information.''

Other Related Rulemaking

Operators should note that we plan to issue a separate AD
rulemaking action (reference Directorate Identifier 2004-NM-55-AD) to
address the identified unsafe condition as it relates to the upper deck
floor beams. Therefore, all requirements from AD 2002-10-10 that relate
to the upper deck floor beams are in that separate AD rulemaking
action.

Differences Between the Proposed AD and Service Information

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 we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by an Authorized Representative
for the Boeing Delegation Option Authorization Organization whom we
have authorized to make those findings.

Change to Existing AD

This proposed AD would retain certain requirements of AD 2002-10-
10. Since AD 2002-10-10 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 in
Requirement in AD 2002-10-10 this proposed AD
------------------------------------------------------------------------
Paragraph (a)......................... Paragraph (f).
Paragraph (b)......................... Paragraph (g).
Paragraph (c)......................... Paragraph (h).
------------------------------------------------------------------------

Costs of Compliance

This proposed AD would affect about 489 airplanes worldwide, and
155 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
Average airplane, Number of
Action Work hours labor rate Parts per U.S. Fleet cost
per hour inspection registered
cycle airplanes
----------------------------------------------------------------------------------------------------------------
Inspections, excluding upper 145 $65 None........... $9,425 155 $1,460,875
deck floor beams, per
inspection cycle (required by
AD 2002-10-10).
Inspections (new proposed AD). 130 65 None........... 8,450 155 1,309,750
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

We have determined that this 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 39-12756 (67 FR
36081, May 23, 2002) and adding the following new airworthiness
directive (AD):

Boeing: Docket No. FAA-2005-20880; Directorate Identifier 2003-NM-
229-AD.

Comments Due Date

(a) The Federal Aviation Administration must receive comments on
this airworthiness directive (AD) action by May 26, 2005.

Affected ADs

(b) This AD supersedes AD 2002-10-10, amendment 39-12756 (67 FR
36081, May 23, 2002).

Applicability

(c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, -
200B, and -300 series airplanes; and Model 747SP and 747SR series
airplanes; certificated in any category; identified in Boeing
Service Bulletin 747-53A2349, Revision 2, dated April 3, 2003.

Unsafe Condition

(d) This AD was prompted by the results of fatigue testing of
the fuselage structure of a Boeing Model 747SR series airplane. We
are issuing this AD to prevent the loss of the structural integrity
of the fuselage, which could result in rapid depressurization of the
airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within

[[Page 18335]]

the compliance times specified, unless the actions have already been
done.

Restatement of Requirements of AD 2002-10-10 (Excluding Upper Deck
Floor Beams)

Repetitive Inspections

(f) Prior to the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993 (the effective date
of AD 93-08-12, amendment 39-8559), whichever occurs later, unless
accomplished previously within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Perform
an internal detailed inspection to detect cracks in the areas of the
fuselage internal structure specified in paragraphs (f)(1) through
(f)(6) of this AD; in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the
effective date of this AD, only Revision 2 of Boeing Service
Bulletin 747-53A2349 may be used. Continue doing the inspections
until the inspections required by paragraph (i) of this AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and 400 bulkheads.
(6) Main entry doors.

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.''

(g) Prior to the accumulation of 25,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993, whichever is later,
unless already done within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Do an
internal detailed inspection to detect cracks in the Section 46
upper lobe frames, in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; or Boeing Service
Bulletin 747-53A2349, Revision 2, dated April 3, 2003. After the
effective date of this AD, only Revision 2 of Boeing Service
Bulletin 747-53A2349 may be used.

Repair

(h) Before further flight, repair any cracks detected during the
inspections done per paragraph (f) or (g) of this AD, in accordance
with a method approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according to data meeting the
certification basis of the airplane approved a Boeing Company
Designated Engineering Representative (DER) who has been authorized
by the Manager, Seattle ACO, to make such findings; or by an
Authorized Representative (AR) for the Boeing Delegation Option
Authorization (DOA) 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.

New Requirements of This AD

Repetitive Inspections

(i) Do an internal detailed inspection to detect cracking in the
areas of the fuselage internal structure specified in paragraphs
(i)(1), (i)(2), (i)(3), and (i)(5) of this AD, and internal and
external detailed inspections of the areas specified in paragraphs
(i)(4), (i)(6), and (i)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin 747-53A2349, Revision 2,
dated April 3, 2003. Do the inspections at the applicable time
specified in paragraph (j) of this AD. Accomplishment of these
inspections terminates the requirements of paragraph (f) of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall panels, and the STA 360
and 380 floor beams. These areas include the Section 41 body station
260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door cutout.
(j) Do the inspections required by paragraph (i) of this AD at
the applicable time specified in paragraph (j)(1), (j)(2), or (j)(3)
of this AD. Repeat the inspections thereafter at intervals not to
exceed 3,000 flight cycles.
(1) For airplanes on which the inspections required by
paragraphs (f)(1), (f)(2), (f)(3), (f)(4), and (f)(6) of this AD
have been done before the effective date of this AD, but the
inspections required by paragraphs (i)(5) and (i)(7) of this AD have
not been done: Within 3,000 flight cycles since accomplishment of
the most recent inspection required by paragraphs (f)(1), (f)(2),
(f)(3), (f)(4), and (f)(6) of this AD.
(2) For airplanes on which the inspections required by
paragraphs (i)(5) and (i)(7) have been done before the effective
date of this AD: Within 3,000 flight cycles since accomplishment of
the most recent inspection required by paragraphs (i)(5) and (i)(7)
of this AD, or within 1,000 flight cycles after the effective date
of this AD, whichever is later.
(3) For airplanes on which the inspections required by paragraph
(f) of this AD have not been done before the effective date of this
AD: Prior to the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after the effective date of this AD,
whichever is later.

Repair

(k) Before further flight, repair any cracking found during any
inspection required by paragraph (i) of this AD in accordance with
Boeing Service Bulletin 747-53A2349, Revision 2, dated April 3,
2003. Where the service bulletin specifies to contact Boeing for
repair instructions, repair in accordance with a method approved by
the Manager, Seattle ACO; or in accordance with data meeting the
type certification basis of the airplane, and that have been
approved by an AR for the Boeing DOA who has been authorized by the
FAA to make those findings. For a repair method to be approved by
the Manager, Seattle ACO, as required by this paragraph, the
approval letter must specifically reference this AD.

Actions Previously Accomplished

(l) Inspections required by paragraph (i) of this AD,
accomplished before the effective date of this AD, in accordance
with the Accomplishment Instructions of Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; or Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; are acceptable for
compliance with the corresponding action required by paragraph (i)
of this AD.

Alternative Methods of Compliance (AMOCs)

(m)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(2) Alternative methods of compliance and FAA-approved repairs,
approved previously in accordance with AD 2002-10-10 or AD 93-08-12,
are approved as alternative methods of compliance with the
corresponding requirements of this AD.

Issued in Renton, Washington, on April 1, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-7155 Filed 4-8-05; 8:45 am]
BILLING CODE 4910-13-P

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