Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 45949-45952 [E7-16104]

Download as PDF Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules substantive response in a notice-andcomment process. For example, a substantive response is required when: (a) The comment causes the NRC staff to reevaluate (or reconsider) its position or conduct additional analysis; (b) The comment raises an issue serious enough to warrant a substantive response to clarify or complete the record; or (c) The comment raises a relevant issue that was not previously addressed or considered by the NRC staff. (2) The comment proposes a change or an addition to the rule, and it is apparent that the rule would be ineffective or unacceptable without incorporation of the change or addition. (3) The comment causes the NRC staff to make a change (other than editorial) to the rule, CoC, or TS. For additional procedural information and the regulatory analysis, see the direct final rule published in the Rules and Regulations section of this Federal Register. (42 U.S.C. 4332); secs. 131, 132, 133, 135, 137, 141, Pub. L. 97–425, 96 Stat. 2229, 2230, 2232, 2241; sec. 148, Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10151, 10152, 10153, 10155, 10157, 10161, 10168); sec. 1704, 112 Stat. 2750 (44 U.S.C. 3504 note); sec. 651(e), Pub. L. 109–58, 119 Stat. 806–10 (42 U.S.C. 2014, 2021, 2021b, 2111). Section 72.44(g) also issued under secs. 142(b) and 148(c), (d), Pub. L. 100–203, 101 Stat. 1330–232, 1330–236 (42 U.S.C. 10162(b), 10168(c),(d)). Section 72.46 also issued under sec. 189, 68 Stat. 955 (42 U.S.C. 2239); sec. 134, Pub. L. 97–425, 96 Stat. 2230 (42 U.S.C. 10154). Section 72.96(d) also issued under sec. 145(g), Pub. L. 100–203, 101 Stat. 1330–235 (42 U.S.C. 10165(g)). Subpart J also issued under secs. 2(2), 2(15), 2(19), 117(a), 141(h), Pub. L. 97–425, 96 Stat. 2202, 2203, 2204, 2222, 2244 (42 U.S.C. 10101, 10137(a), 10161(h)). Subparts K and L are also issued under sec. 133, 98 Stat. 2230 (42 U.S.C. 10153) and sec. 218(a), 96 Stat. 2252 (42 U.S.C. 10198). 2. In § 72.214, Certificate of Compliance 1027 is revised to read as follows: § 72.214 List of approved spent fuel storage casks. List of Subjects In 10 CFR Part 72 Administrative practice and procedure, Criminal penalties, Manpower training programs, Nuclear materials, Occupational safety and health, Penalties, Radiation protection, Reporting and recordkeeping requirements, Security measures, Spent fuel, Whistleblowing. For the reasons set out in the preamble and under the authority of the Atomic Energy Act of 1954, as amended; the Energy Reorganization Act of 1974, as amended; the Nuclear Waste Policy Act of 1982, as amended; and 5 U.S.C. 553; the NRC is proposing to adopt the following amendments to 10 CFR part 72. PART 72—LICENSING REQUIREMENTS FOR THE INDEPENDENT STORAGE OF SPENT NUCLEAR FUEL, HIGH-LEVEL RADIOACTIVE WASTE, AND REACTOR-RELATED GREATER THAN CLASS C WASTE * * * * * Certificate Number: 1027. Initial Certificate Effective Date: May 30, 2000. Amendment Number 1 Effective Date: October 30, 2007. SAR Submitted by: Transnuclear, Inc. SAR Title: Final Safety Analysis Report for the TN–68 Dry Storage Cask. Docket Number: 72–1027. Certificate Expiration Date: May 28, 2020. Model Number: TN–68. * * * * * Dated at Rockville, Maryland, this 31st day of July, 2007. For the Nuclear Regulatory Commission. Martin J. Virgilio, Acting Executive Director for Operations. [FR Doc. E7–16135 Filed 8–15–07; 8:45 am] BILLING CODE 7590–01–P DEPARTMENT OF TRANSPORTATION rwilkins on PROD1PC63 with PROPOSALS 1. The authority citation for part 72 continues to read as follows: Federal Aviation Administration Authority: Secs. 51, 53, 57, 62, 63, 65, 69, 81, 161, 182, 183, 184, 186, 187, 189, 68 Stat. 929, 930, 932, 933, 934, 935, 948, 953, 954, 955, as amended; sec. 234, 83 Stat. 444, as amended (42 U.S.C. 2071, 2073, 2077, 2092, 2093, 2095, 2099, 2111, 2201, 2232, 2233, 2234, 2236, 2237, 2238, 2282); sec. 274, Pub. L. 86–373, 73 Stat. 688, as amended (42 U.S.C. 2021); sec. 201, as amended, 202, 206, 88 Stat. 1242; as amended, 1244, 1246 (42 U.S.C. 5841, 5842, 5846); Pub. L. 95–601, sec. 10, 92 Stat. 2951, as amended by Pub. L. 102– 486, sec. 7902, 106 Stat. 3123 (42 U.S.C. 5851); sec. 102, Pub. L. 91–190, 83 Stat. 853 14 CFR Part 39 VerDate Aug<31>2005 17:19 Aug 15, 2007 Jkt 211001 [Docket No. FAA–2007–28942; Directorate Identifier 2007–NM–093–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 45949 Notice of proposed rulemaking (NPRM). ACTION: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This proposed AD would require repetitive detailed and highfrequency eddy current inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the station (STA) 259.5 circumferential butt splice, and repair if necessary. This proposed AD would also require a preventive modification, which would eliminate the need for the repetitive inspections. This proposed AD results from a report that an operator found multiple cracks in the fuselage skin of a Model 737–200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers 19 and 24. We are proposing this AD to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. DATES: We must receive comments on this proposed AD by October 1, 2007. 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6447; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: E:\FR\FM\16AUP1.SGM 16AUP1 45950 Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules 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 in the ADDRESSES section. Include the docket number ‘‘Docket No. FAA–2007–28942; Directorate Identifier 2007–NM–093– 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 that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you may visit https:// dms.dot.gov. Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after the Docket Management System receives them. Discussion We have received a report indicating that an operator found multiple cracks in the fuselage skin of a Model 737–200 airplane that had accumulated 69,350 total flight cycles. The cracking was found at the forward fastener row of the station (STA) 259.5 circumferential butt splice between stringers 19 and 24, and some cracks had joined into one large crack. This condition, if not corrected, could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 737–53– 1267, dated November 28, 2006. The service bulletin describes procedures for doing repetitive detailed and highfrequency eddy current (HFEC) surface inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the STA 259.5 circumferential butt splice, and applicable repair if necessary. Certain areas of the circumferential butt splice are those described in the Accomplishment Instructions of Service Bulletin 737–53–1267 as areas that have not had a preventive modification installed in accordance with Boeing Service Bulletin 737–53–1076, or have not had a Boeing, FAA-approved repair accomplished. The service bulletin also describes procedures for doing a preventive modification of certain areas of the STA 259.5 circumferential butt splice, including removing the existing fasteners, doing an HFEC rotary probe inspection of the fastener holes, and, if no crack is found, oversizing the holes and installing new protruding head fasteners. The preventive modification eliminates the need for the repetitive inspections. The service bulletin specifies compliance times that depend upon the number of total flight cycles accumulated by the airplane. Compliance times for doing the initial inspections begin at or before the accumulation of 50,000 total flight cycles, with grace periods ranging between 500 and 4,500 flight cycles after the release date of the service bulletin. The service bulletin specifies that repetitive inspections shall be done thereafter at intervals of 9,000 flight cycles, until the preventive modification is done. The service bulletin specifies that all repairs are to be done before further flight and that the preventive modification is to be done before the accumulation of 75,000 total flight cycles or within 6,000 flight cycles after the release date of the service bulletin, whichever comes later. 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 airplanes of this same type design. For this reason, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously. Costs of Compliance There are about 2,150 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 $80 per work hour. Required parts would be supplied by the operator. ESTIMATED COSTS Work hours Action Inspection ............................................ Preventive modification ....................... 5 24 rwilkins on PROD1PC63 with PROPOSALS 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 VerDate Aug<31>2005 17:19 Aug 15, 2007 Jkt 211001 Number of U.S.-registered airplanes Cost per airplane $400, per inspection cycle ................. $1,920 ................................................. 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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 654 654 Fleet cost $261,600, per inspection cycle. $1,255,680. 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 E:\FR\FM\16AUP1.SGM 16AUP1 45951 Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules § 39.13 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 and placed it in the AD docket. 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. [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28942; Directorate Identifier 2007–NM–093–AD. Comments Due Date (a) The FAA must receive comments on this AD action by October 1, 2007. Affected ADs (b) Accomplishing repairs and modifications described in paragraphs (f) and (g) of this AD is considered acceptable for compliance with repair requirements of paragraphs (f) and (g) of AD 92–25–09, amendment 39–8424, for the areas of the station (STA) 259.5 circumferential butt splice only. Applicability (c) This AD applies to Boeing Model 737– 100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 737–53–1267, dated November 28, 2006. Unsafe Condition (d) This AD results from a report that an operator found multiple cracks in the fuselage skin of a Model 737–200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers 19 and 24. We are issuing this AD to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections (f) At the applicable initial compliance time specified in paragraph 1.E. ‘‘Compliance’’ of Boeing Special Attention Service Bulletin 737–53–1267, dated November 28, 2006, except as provided by paragraph (j) of this AD: Do detailed and high-frequency eddy current inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the station (STA) 259.5 circumferential butt splice, by doing all of the actions specified in Part 1 of the Accomplishment Instructions of the service bulletin, except as provided by paragraph (i) of this AD. Repeat the inspections thereafter at the intervals specified in paragraph 1.E. of the service bulletin. Doing the preventive modification specified in paragraph (h) of this AD terminates the repetitive inspection requirements of this paragraph. Repair (g) If any crack is found during any inspection required by this AD, before further flight, repair in accordance with Part 1 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53– 1267, dated November 28, 2006. Preventive Modification (h) At the compliance time specified in paragraph 1.E. of Boeing Special Attention Service Bulletin 737–53–1267, dated November 28, 2006, except as provided by paragraph (j) of this AD: Do the preventive modification in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53– 1267, dated November 28, 2006. Doing the preventive modification terminates the repetitive inspections required by paragraph (f) of this AD. Modification or Repair Done in Accordance with AD 92–25–09 (i) Inspections described by paragraph (f) of this AD are not required for areas of the STA 259.5 circumferential butt splice that have been modified in accordance with the service information specified in Table 1 of this AD. (Boeing Service Bulletin 737–53–1076, Revision 4, dated September 26, 1991, is cited as an appropriate source of service information for doing certain requirements of AD 92–25–09.) TABLE 1.—SERVICE INFORMATION Boeing Service Bulletin 737–53–1076 737–53–1076 737–53–1076 737–53–1076 737–53–1076 ................................................................................................................................... ................................................................................................................................... ................................................................................................................................... ................................................................................................................................... ................................................................................................................................... rwilkins on PROD1PC63 with PROPOSALS Compliance Times (j) Where the service bulletin specifies compliance times relative to the release date of Boeing Special Attention Service Bulletin 737–53–1267, dated November 28, 2006, this AD requires compliance at compliance times relative to the effective date of this AD. VerDate Aug<31>2005 Revision level 17:19 Aug 15, 2007 Jkt 211001 Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Date 4 ................................ 3 ................................ 2 ................................ 1 ................................ Original Issue ............ September 26, 1991. September 20, 1990. February 8, 1990. November 23, 1988. October 30, 1986. 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing E:\FR\FM\16AUP1.SGM 16AUP1 45952 Federal Register / Vol. 72, No. 158 / Thursday, August 16, 2007 / Proposed Rules Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Issued in Renton, Washington, on July 30, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–16104 Filed 8–15–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration • Fax: (202) 493–2251. • Hand Delivery: Room W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this proposed AD. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 Comments Invited [Docket No. FAA–2007–28996; Directorate Identifier 2006–NM–217–AD] We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed in the ADDRESSES section. Include the docket number ‘‘FAA–2007–28996; Directorate Identifier 2006–NM–217–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 that Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You 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. RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for all Airbus Model A310 series airplanes. This proposed AD would require revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new and revised structural inspections and inspection intervals. This proposed AD results from issuance of new and revised structural inspections and inspection intervals. We are proposing this AD to detect and correct fatigue cracking, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by September 17, 2007. 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. rwilkins on PROD1PC63 with PROPOSALS ADDRESSES: VerDate Aug<31>2005 17:19 Aug 15, 2007 Jkt 211001 Examining the Docket You may examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Operations office (telephone (800) 647–5527) is located on the ground floor of the West Building at the DOT street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 the Docket Management System receives them. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, notified us that an unsafe condition may exist on all Airbus Model A310 series airplanes. The EASA advises that Airbus has issued new and revised structural inspections and inspection intervals to detect and correct fatigue cracking. This condition, if not corrected, could result in reduced structural integrity of the airplane. Relevant Service Information Airbus has issued A310 Airworthiness Limitation Items (ALI) Document, AI/SE–M2/95A.0263/06, Issue 6, dated April 2006 (approved by the EASA on May 31, 2006) (hereafter referred to as ‘‘Issue 6 of the ALI’’). That ALI document describes fatigue-related structural inspections arising from the evaluation of damage tolerance and widespread fatigue damage. Airbus has also issued Temporary Revision (TR) 6.1, dated November 2006 (approved by the EASA on December 12, 2006), to Issue 6 of the ALI. Airbus TR 6.1 provides new and revised inspections to address certification of the new Model A310–300 weight variant airplanes (Airbus Modification 13302). The applicability, limit of validity, program rules, program notes, and definitions stated in Issue 6 of the ALI remain valid. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. The EASA mandated the service information and issued airworthiness directive 2006–0260, dated August 25, 2006, to ensure the continued airworthiness of these airplanes in the European Union. FAA’s Determination and Requirements of the Proposed AD This airplane model is manufactured in France and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. As described in FAA Order 8100.14A, ‘‘Interim Procedures for Working with the European Community on Airworthiness Certification and Continued Airworthiness,’’ dated August 12, 2005, the EASA has kept the FAA informed of the situation described above. We have examined the EASA’s findings, evaluated all pertinent information, and determined that we need to issue an AD E:\FR\FM\16AUP1.SGM 16AUP1

Agencies

[Federal Register Volume 72, Number 158 (Thursday, August 16, 2007)]
[Proposed Rules]
[Pages 45949-45952]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-16104]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28942; Directorate Identifier 2007-NM-093-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-100, -200, -200C, -
300, -400, and -500 Series Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 
series airplanes. This proposed AD would require repetitive detailed 
and high-frequency eddy current inspections for cracking around the 
heads of the fasteners on the forward fastener row of certain areas of 
the station (STA) 259.5 circumferential butt splice, and repair if 
necessary. This proposed AD would also require a preventive 
modification, which would eliminate the need for the repetitive 
inspections. This proposed AD results from a report that an operator 
found multiple cracks in the fuselage skin of a Model 737-200 airplane, 
at the forward fastener row of the STA 259.5 circumferential butt 
splice between stringers 19 and 24. We are proposing this AD to prevent 
cracking of the STA 259.5 circumferential butt splice, which could 
result in loss of structural integrity of the fuselage skin and 
possible loss of cabin pressure.

DATES: We must receive comments on this proposed AD by October 1, 2007.

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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room W12-140 on the ground floor of the 
West Building, 1200 New Jersey Avenue, SE., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for the service information identified in this 
proposed AD.

FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6447; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

[[Page 45950]]

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 in the ADDRESSES section. Include the docket number ``Docket No. 
FAA-2007-28942; Directorate Identifier 2007-NM-093-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 
that Web site, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You may review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
may visit https://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The 
Docket Operations office (telephone (800) 647-5527) is located on the 
ground floor of the West Building at the DOT street address stated in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after the Docket Management System receives them.

Discussion

    We have received a report indicating that an operator found 
multiple cracks in the fuselage skin of a Model 737-200 airplane that 
had accumulated 69,350 total flight cycles. The cracking was found at 
the forward fastener row of the station (STA) 259.5 circumferential 
butt splice between stringers 19 and 24, and some cracks had joined 
into one large crack. This condition, if not corrected, could result in 
loss of structural integrity of the fuselage skin and possible loss of 
cabin pressure.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 737-53-
1267, dated November 28, 2006. The service bulletin describes 
procedures for doing repetitive detailed and high-frequency eddy 
current (HFEC) surface inspections for cracking around the heads of the 
fasteners on the forward fastener row of certain areas of the STA 259.5 
circumferential butt splice, and applicable repair if necessary. 
Certain areas of the circumferential butt splice are those described in 
the Accomplishment Instructions of Service Bulletin 737-53-1267 as 
areas that have not had a preventive modification installed in 
accordance with Boeing Service Bulletin 737-53-1076, or have not had a 
Boeing, FAA-approved repair accomplished.
    The service bulletin also describes procedures for doing a 
preventive modification of certain areas of the STA 259.5 
circumferential butt splice, including removing the existing fasteners, 
doing an HFEC rotary probe inspection of the fastener holes, and, if no 
crack is found, oversizing the holes and installing new protruding head 
fasteners. The preventive modification eliminates the need for the 
repetitive inspections.
    The service bulletin specifies compliance times that depend upon 
the number of total flight cycles accumulated by the airplane. 
Compliance times for doing the initial inspections begin at or before 
the accumulation of 50,000 total flight cycles, with grace periods 
ranging between 500 and 4,500 flight cycles after the release date of 
the service bulletin. The service bulletin specifies that repetitive 
inspections shall be done thereafter at intervals of 9,000 flight 
cycles, until the preventive modification is done. The service bulletin 
specifies that all repairs are to be done before further flight and 
that the preventive modification is to be done before the accumulation 
of 75,000 total flight cycles or within 6,000 flight cycles after the 
release date of the service bulletin, whichever comes later.
    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 airplanes 
of this same type design. For this reason, we are proposing this AD, 
which would require accomplishing the actions specified in the service 
information described previously.

Costs of Compliance

    There are about 2,150 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 $80 per work hour. Required parts would be supplied by the 
operator.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                         Number of U.S.-
                Action                  Work       Cost per airplane       registered           Fleet cost
                                        hours                               airplanes
----------------------------------------------------------------------------------------------------------------
Inspection...........................       5  $400, per inspection                 654  $261,600, per
                                                cycle.                                    inspection cycle.
Preventive modification..............      24  $1,920..................             654  $1,255,680.
----------------------------------------------------------------------------------------------------------------

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

[[Page 45951]]

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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-28942; Directorate Identifier 2007-NM-
093-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
1, 2007.

Affected ADs

    (b) Accomplishing repairs and modifications described in 
paragraphs (f) and (g) of this AD is considered acceptable for 
compliance with repair requirements of paragraphs (f) and (g) of AD 
92-25-09, amendment 39-8424, for the areas of the station (STA) 
259.5 circumferential butt splice only.

Applicability

    (c) This AD applies to Boeing Model 737-100, -200, -200C, -300, 
-400, and -500 series airplanes, certificated in any category, as 
identified in Boeing Special Attention Service Bulletin 737-53-1267, 
dated November 28, 2006.

Unsafe Condition

    (d) This AD results from a report that an operator found 
multiple cracks in the fuselage skin of a Model 737-200 airplane, at 
the forward fastener row of the STA 259.5 circumferential butt 
splice between stringers 19 and 24. We are issuing this AD to 
prevent cracking of the STA 259.5 circumferential butt splice, which 
could result in loss of structural integrity of the fuselage skin 
and possible loss of cabin pressure.

Compliance

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

Inspections

    (f) At the applicable initial compliance time specified in 
paragraph 1.E. ``Compliance'' of Boeing Special Attention Service 
Bulletin 737-53-1267, dated November 28, 2006, except as provided by 
paragraph (j) of this AD: Do detailed and high-frequency eddy 
current inspections for cracking around the heads of the fasteners 
on the forward fastener row of certain areas of the station (STA) 
259.5 circumferential butt splice, by doing all of the actions 
specified in Part 1 of the Accomplishment Instructions of the 
service bulletin, except as provided by paragraph (i) of this AD. 
Repeat the inspections thereafter at the intervals specified in 
paragraph 1.E. of the service bulletin. Doing the preventive 
modification specified in paragraph (h) of this AD terminates the 
repetitive inspection requirements of this paragraph.

Repair

    (g) If any crack is found during any inspection required by this 
AD, before further flight, repair in accordance with Part 1 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 737-53-1267, dated November 28, 2006.

Preventive Modification

    (h) At the compliance time specified in paragraph 1.E. of Boeing 
Special Attention Service Bulletin 737-53-1267, dated November 28, 
2006, except as provided by paragraph (j) of this AD: Do the 
preventive modification in accordance with the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 737-53-
1267, dated November 28, 2006. Doing the preventive modification 
terminates the repetitive inspections required by paragraph (f) of 
this AD.

Modification or Repair Done in Accordance with AD 92-25-09

    (i) Inspections described by paragraph (f) of this AD are not 
required for areas of the STA 259.5 circumferential butt splice that 
have been modified in accordance with the service information 
specified in Table 1 of this AD. (Boeing Service Bulletin 737-53-
1076, Revision 4, dated September 26, 1991, is cited as an 
appropriate source of service information for doing certain 
requirements of AD 92-25-09.)

                                          Table 1.--Service Information
----------------------------------------------------------------------------------------------------------------
        Boeing Service Bulletin                    Revision level                            Date
----------------------------------------------------------------------------------------------------------------
737-53-1076...........................  4..................................  September 26, 1991.
737-53-1076...........................  3..................................  September 20, 1990.
737-53-1076...........................  2..................................  February 8, 1990.
737-53-1076...........................  1..................................  November 23, 1988.
737-53-1076...........................  Original Issue.....................  October 30, 1986.
----------------------------------------------------------------------------------------------------------------

Compliance Times

    (j) Where the service bulletin specifies compliance times 
relative to the release date of Boeing Special Attention Service 
Bulletin 737-53-1267, dated November 28, 2006, this AD requires 
compliance at compliance times relative to the effective date of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing

[[Page 45952]]

Commercial Airplanes Delegation Option Authorization Organization 
who has been authorized by the Manager, Seattle ACO, to make those 
findings. For a repair method to be approved, the repair must meet 
the certification basis of the airplane, and the approval must 
specifically refer to this AD.

    Issued in Renton, Washington, on July 30, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-16104 Filed 8-15-07; 8:45 am]
BILLING CODE 4910-13-P
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