Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes, 65446-65449 [E7-22724]

Download as PDF 65446 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Docket Number Change We are transferring the docket for this AD to the Federal Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2007–0108. The old Docket No. became the Directorate Identifier, which is 2001–NE–15–AD. rmajette on PROD1PC64 with RULES 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 AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12405 (66 FR 44297, August 23, 2001), and by adding a new airworthiness directive, Amendment 39–15270, to read as follows: I 2007–24–04 CFM International, S.A.: Amendment 39–15270. Docket No. FAA–2007–0108; Directorate Identifier 2001–NE–15–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 6, 2007. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) None. Related Information (j) Contact Stephen Sheely, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: stephen.k.sheely@faa.gov; telephone (781) 238–7750; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on November 14, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–22647 Filed 11–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0211; Directorate Identifier 2007–NM–221–AD; Amendment 39–15268; AD 2007–24–02] RIN 2120–AA64 Affected ADs (b) This AD supersedes AD 2001–17–14, Amendment 39–12405. Airworthiness Directives; Boeing Model 737–100, –200, –200C, –300, –400, and –500 Series Airplanes Applicability (c) This AD applies to CFM International, S.A. CFM56–5C4/1 series turbofan engines with low pressure turbine (LPT) conical support, part number (P/N) 337–002–407–0, installed. These engines are installed on, but not limited to, Airbus A340 series airplanes. AGENCY: Unsafe Condition (d) This AD results from CFM International, S.A. performing a life extension study of the LPT conical support, P/N 337–002–407–0. We are issuing this AD to prevent LPT conical supports from remaining in service beyond their certified cyclic life limit, which could result in an uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) Remove LPT conical support, P/N 337– 002–407–0, at or before accumulating 20,000 cycles-since-new (CSN) and replace with a serviceable part. (g) After the effective date of this AD, do not install any LPT conical support, P/N 337–002–407–0, with 20,000 or more CSN, into CFM56–5C4/1 series turbofan engines. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to all Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. The existing AD currently requires repetitive detailed inspections for damage of the electrical wire and sleeve that run to the fuel boost pump through a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; replacement of the sleeve with a new, smaller-diameter sleeve; and related investigative and corrective actions, as applicable. This new AD reduces the inspection threshold for certain airplanes. This AD results from a report of a fuel tank explosion on a Model 727–200F airplane on the ground, and a report of chafed wires and a damaged power cable sleeve of a fuel boost pump discovered during an inspection on a Model 737–300 airplane. (The fuel boost E:\FR\FM\21NOR1.SGM 21NOR1 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations pump installation on certain Model 737 airplanes is almost identical to the installation on Model 727 airplanes.) We are issuing this AD to detect and correct chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. DATES: This AD becomes effective December 6, 2007. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of December 6, 2007. On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 737–28A1263, Revision 1, dated March 19, 2007. We must receive any comments on this AD by January 22, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • 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. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. rmajette on PROD1PC64 with RULES Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Suzanne Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 Washington 98057–3356; telephone (425) 917–6438; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion On May 2, 2007, we issued AD 2007– 11–07, amendment 39–15064 (72 FR 28597, May 22, 2007). (A correction of that AD was published in the Federal Register on August 21, 2007 (72 FR 46559).) That AD applies to all Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. That AD requires repetitive detailed inspections for damage of the electrical wire and sleeve that run to the fuel boost pump through a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; replacement of the sleeve with a new, smaller-diameter sleeve; and related investigative and corrective actions, as applicable. That AD resulted from a report of a fuel tank explosion on a Model 727–200F airplane on the ground, and a report of chafed wires and a damaged power cable sleeve of a fuel boost pump discovered during an inspection on a Model 737–300 airplane. The actions specified in that AD are intended to detect and correct chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arcthrough of the conduit, and consequent fire or explosion of the fuel tank. Actions Since AD Was Issued Since we issued AD 2007–11–07, we were contacted by an operator who misinterpreted the compliance threshold in a way that was not intended. Therefore, we are issuing this new AD to restate certain compliance thresholds in a new way in order to avoid misinterpretation and to ensure continued operational safety of these airplanes. To do so, we have based certain compliance thresholds on previous accomplishment of any revision of Boeing Alert Service Bulletin 737–28A1120 identified in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of This AD. These revisions of Boeing Alert Service Bulletin 737–28A1120 were previously mandated by AD 99–21–15, amendment 39–11360 (64 FR 54763, October 8, 1999) and the two ADs it superseded. AD 99–21–15 was superseded by AD 2007–11–07; therefore, we have not restated the requirements of AD 99–21– 15 in this new AD. Related Rulemaking On May 1, 2007, we issued AD 2007– 11–08, amendment 39–15065 (72 FR 28594, May 22, 2007), which applies to PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 65447 all Boeing Model 727 airplanes. AD 2007–11–08 requires repetitive inspections for damage of the electrical wire and sleeve that run to the fuel boost pump though a conduit in the fuel tank, and arcing damage of the conduit and signs of fuel leakage into the conduit; applicable investigative and corrective actions; and a repetitive engine fuel suction feed operational test. That AD resulted from reports of a fuel tank explosion on a Model 727–200F airplane on the ground; and of chafed wires and a damaged power cable sleeve of a fuel boost pump that were discovered during an inspection required by an existing AD on a Model 737–300 airplane. We issued that AD to detect and correct chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. Relevant Service Information Since we issued AD 2007–11–07, Boeing has issued Service Bulletin 737– 28A1263, Revision 2, dated August 10, 2007. We referred to Boeing Alert Service Bulletin 737–28A1263, Revision 1, dated March 19, 2007, as the appropriate source of service information for accomplishing certain actions in AD 2007–11–07. The procedures in Revision 2 of the service bulletin are essentially the same as those in Revision 1, with several editorial changes such as a revised email address, and the addition of references to AD 2007–11–07. Revision 2 also incorporates alternative methods of compliance (AMOCs) previously approved for AD 2007–11–07. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other airplanes of the same type design. For this reason, we are issuing this AD to supersede AD 2007–11–07. This new AD retains certain requirements of the existing AD. This AD also reduces the compliance threshold for certain airplanes. Interim Action We consider this AD interim action. If final action is later identified, we might consider further rulemaking then. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD; therefore, providing notice and E:\FR\FM\21NOR1.SGM 21NOR1 65448 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations opportunity for public comment before the AD is issued is impracticable, and good cause exists to make this AD effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments before it becomes effective. However, we invite you to send any written data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2007–0211; Directorate Identifier 2007– NM–221–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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. rmajette on PROD1PC64 with RULES Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 For the reasons discussed above, I certify that the 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 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, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by removing amendment 39–15064 (72 FR 28597, May 22, 2007), corrected at 72 FR 46559, August 21, 2007, and adding the following new airworthiness directive (AD): I 2007–24–02 Boeing: Docket No. FAA–2007– 0211; Directorate Identifier 2007–NM– 221–AD; Amendment 39–15268. Effective Date (a) This AD becomes effective December 6, 2007. Affected ADs (b) This AD supersedes AD 2007–11–07. Applicability (c) This AD applies to all Boeing Model 737–100, –200, –200C, –300, –400, and –500 series airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report of a fuel tank explosion on a Model 727–200F airplane on the ground, and a report of chafed wires and a damaged power cable sleeve of a fuel boost pump discovered during an inspection on a Model 737–300 airplane. (The fuel boost pump installation on certain Model 737 airplanes is almost identical to the installation on Model 727 airplanes.) We are issuing this AD to detect PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 and correct chafing of the fuel boost pump electrical wiring and leakage of fuel into the conduit, and to prevent electrical arcing between the wiring and the surrounding conduit, which could result in arc-through of the conduit, and consequent fire or explosion of the fuel tank. 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. Certain Requirements of AD 2007–11–07 Inspection and Related Investigative and Corrective Actions (f) At the applicable time specified by paragraph (f)(1) or (f)(2) of this AD: Do a detailed inspection for damage of the sleeve and electrical wire of the fuel boost pump; and, before further flight, install a new, smaller-diameter sleeve, and do related investigative and corrective actions, as applicable; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–28A1263, Revision 1, dated March 19, 2007; or Boeing Service Bulletin 737–28A1263, Revision 2, dated August 10, 2007. After the effective date of this AD, Revision 2 must be used. Thereafter, repeat the detailed inspection at intervals not to exceed 15,000 flight hours. (1) For Model 737–100, –200, –300, –400, and –500 series airplanes: At the time specified in paragraph (i) or (j) of this AD, as applicable. (2) For Model 737–200C series airplanes: Within 120 days after June 6, 2007 (the effective date of AD 2007–11–07), or within 5,000 flight hours after the last inspection or repair done in accordance with any version of Boeing Alert Service Bulletin 737–28– 1120, whichever occurs later. Inspection Report and Disposition of Damaged Parts (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD: Submit a report of the findings (both positive and negative) of any inspection required by paragraph (f) of this AD and send any damaged parts to the manufacturer, as described in Boeing Alert Service Bulletin 737–28A1263, Revision 1, dated March 19, 2007. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (1) For any inspection done on or after June 6, 2007: Submit the report within 30 days after the inspection. (2) For any inspection done before June 6, 2007: Submit the report within 30 days after June 6, 2007. Credit for Actions Done Using Previous Service Information (h) Actions accomplished before June 6, 2007, in accordance with Boeing Service E:\FR\FM\21NOR1.SGM 21NOR1 Federal Register / Vol. 72, No. 224 / Wednesday, November 21, 2007 / Rules and Regulations Bulletin 737–28A1263, dated February 19, 2007, are considered acceptable for compliance with the corresponding actions specified in this AD. New Requirements of This AD Previously Required Inspection at New Compliance Times (i) For Model 737–100, –200, –300, –400, and –500 series airplanes having line numbers 1 through 3072 inclusive: Within 120 days after the effective date of this AD, or within 5,000 flight hours after the last inspection or repair done in accordance with any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD, whichever occurs later, do the actions specified in paragraph (f) of this AD. (1) Boeing Alert Service Bulletin 737– 28A1120, dated April 24, 1998, as revised by Notices of Status Change NSC 01, dated May 7, 1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998. (2) Boeing Alert Service Bulletin 737– 28A1120, Revision 1, dated May 28, 1998. (3) Boeing Alert Service Bulletin 737– 28A1120, Revision 2, dated November 26, 1998. (4) Boeing Service Bulletin 737–28A1120, Revision 3, dated April 26, 2001. (j) For Model 737–100, –200, –300, –400, and –500 series airplanes having line numbers 3073 and subsequent: At the applicable time specified in paragraph (j)(1) or (j)(2) of this AD, do the actions specified in paragraph (f) of this AD. (1) For airplanes on which the inspection or repair specified in any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD, has been done as of the effective date of this AD: Within 120 days after the effective date of this AD or 5,000 flight hours after the last inspection done in accordance with any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD, whichever occurs later. (2) For airplanes on which the inspection or repair specified in any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of this AD, has not been done as of the effective date of this AD: Before the accumulation of 5,000 total flight hours, or within 120 days after the effective date of this AD, whichever occurs later. Inspection Report and Disposition of Damaged Parts (k) For Model 737–100, –200, –300, –400, and –500 series airplanes: At the applicable time specified in paragraph (k)(1) or (k)(2) of this AD, submit a report of the findings (both positive and negative) of any inspection required by paragraph (i) or (j) of this AD and send any damaged parts to the manufacturer, as described in Boeing Service Bulletin 737– 28A1263, Revision 2, dated August 10, 2007. The report must include the inspection results, a description of any discrepancies found, the airplane serial number, and the number of landings and flight hours on the airplane. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD 65449 and has assigned OMB Control Number 2120–0056. (1) For any inspection done after the effective date of this AD: Submit the report within 30 days after the inspection. (2) For any inspection done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (AMOCs) (l)(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) AMOCs approved previously in accordance with AD 99–21–15, amendment 39–11360, and AD 2007–11–07 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (m) You must use applicable Boeing service bulletins specified in Table 1 of this AD to perform the actions that are required by this AD, unless the AD specifies otherwise. TABLE 1.—ALL MATERIAL INCORPORATED BY REFERENCE Revision level Service Bulletin rmajette on PROD1PC64 with RULES Boeing Alert Service Bulletin 737–28A1263 .................................................................................................. Boeing Service Bulletin 737–28A1263 .......................................................................................................... (1) The Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 737–28A1263, Revision 2, dated August 10, 2007, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 737–28A1263, Revision 1, dated March 19, 2007. (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124– 2207, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. VerDate Aug<31>2005 15:23 Nov 20, 2007 Jkt 214001 Issued in Renton, Washington, on November 8, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–22724 Filed 11–20–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 77 [Docket No. FAA–2004–16982; Notice No. 07–16] Colo Void Clause Coalition; Antenna Systems Co-Location; Voluntary Best Practices Federal Aviation Administration (FAA); DOT. ACTION: Notice of amended policy. AGENCY: PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Date 1 2 March 19, 2007. August 10, 2007. SUMMARY: On April 27, 2004, the FAA revised its policy regarding the colocation of antenna systems on existing structures previously studied by the FAA. Based on various additional comments from industry regarding the initial policy, the FAA finds that further modifications to this policy are necessary. This policy is effective on November 21, 2007. DATES: FOR FURTHER INFORMATION CONTACT: ´ Rene J. Balanga, ATC Spectrum Engineering Services, Spectrum Assignment and Engineering Office, Federal Aviation Administration, 800 Independence Ave., SW., Washington, DC 20591, Telephone (202) 267–3819 or (202) 267–9710. SUPPLEMENTARY INFORMATION: E:\FR\FM\21NOR1.SGM 21NOR1

Agencies

[Federal Register Volume 72, Number 224 (Wednesday, November 21, 2007)]
[Rules and Regulations]
[Pages 65446-65449]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-22724]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0211; Directorate Identifier 2007-NM-221-AD; 
Amendment 39-15268; AD 2007-24-02]
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: Final rule; request for comments.

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

Summary: The FAA is superseding an existing airworthiness directive 
(AD) that applies to all Model 737-100, -200, -200C, -300, -400, and -
500 series airplanes. The existing AD currently requires repetitive 
detailed inspections for damage of the electrical wire and sleeve that 
run to the fuel boost pump through a conduit in the fuel tank, and 
arcing damage of the conduit and signs of fuel leakage into the 
conduit; replacement of the sleeve with a new, smaller-diameter sleeve; 
and related investigative and corrective actions, as applicable. This 
new AD reduces the inspection threshold for certain airplanes. This AD 
results from a report of a fuel tank explosion on a Model 727-200F 
airplane on the ground, and a report of chafed wires and a damaged 
power cable sleeve of a fuel boost pump discovered during an inspection 
on a Model 737-300 airplane. (The fuel boost

[[Page 65447]]

pump installation on certain Model 737 airplanes is almost identical to 
the installation on Model 727 airplanes.) We are issuing this AD to 
detect and correct chafing of the fuel boost pump electrical wiring and 
leakage of fuel into the conduit, and to prevent electrical arcing 
between the wiring and the surrounding conduit, which could result in 
arc-through of the conduit, and consequent fire or explosion of the 
fuel tank.

DATES: This AD becomes effective December 6, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of December 6, 
2007.
    On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of the 
Federal Register approved the incorporation by reference of Boeing 
Alert Service Bulletin 737-28A1263, Revision 1, dated March 19, 2007.
    We must receive any comments on this AD by January 22, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this AD, contact Boeing 
Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT:  Suzanne Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 
(425) 917-6438; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 2, 2007, we issued AD 2007-11-07, amendment 39-15064 (72 FR 
28597, May 22, 2007). (A correction of that AD was published in the 
Federal Register on August 21, 2007 (72 FR 46559).) That AD applies to 
all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series 
airplanes. That AD requires repetitive detailed inspections for damage 
of the electrical wire and sleeve that run to the fuel boost pump 
through a conduit in the fuel tank, and arcing damage of the conduit 
and signs of fuel leakage into the conduit; replacement of the sleeve 
with a new, smaller-diameter sleeve; and related investigative and 
corrective actions, as applicable. That AD resulted from a report of a 
fuel tank explosion on a Model 727-200F airplane on the ground, and a 
report of chafed wires and a damaged power cable sleeve of a fuel boost 
pump discovered during an inspection on a Model 737-300 airplane. The 
actions specified in that AD are intended to detect and correct chafing 
of the fuel boost pump electrical wiring and leakage of fuel into the 
conduit, and to prevent electrical arcing between the wiring and the 
surrounding conduit, which could result in arc-through of the conduit, 
and consequent fire or explosion of the fuel tank.

Actions Since AD Was Issued

    Since we issued AD 2007-11-07, we were contacted by an operator who 
misinterpreted the compliance threshold in a way that was not intended. 
Therefore, we are issuing this new AD to restate certain compliance 
thresholds in a new way in order to avoid misinterpretation and to 
ensure continued operational safety of these airplanes. To do so, we 
have based certain compliance thresholds on previous accomplishment of 
any revision of Boeing Alert Service Bulletin 737-28A1120 identified in 
paragraph (i)(1), (i)(2), (i)(3), or (i)(4) of This AD. These revisions 
of Boeing Alert Service Bulletin 737-28A1120 were previously mandated 
by AD 99-21-15, amendment 39-11360 (64 FR 54763, October 8, 1999) and 
the two ADs it superseded. AD 99-21-15 was superseded by AD 2007-11-07; 
therefore, we have not restated the requirements of AD 99-21-15 in this 
new AD.

Related Rulemaking

    On May 1, 2007, we issued AD 2007-11-08, amendment 39-15065 (72 FR 
28594, May 22, 2007), which applies to all Boeing Model 727 airplanes. 
AD 2007-11-08 requires repetitive inspections for damage of the 
electrical wire and sleeve that run to the fuel boost pump though a 
conduit in the fuel tank, and arcing damage of the conduit and signs of 
fuel leakage into the conduit; applicable investigative and corrective 
actions; and a repetitive engine fuel suction feed operational test. 
That AD resulted from reports of a fuel tank explosion on a Model 727-
200F airplane on the ground; and of chafed wires and a damaged power 
cable sleeve of a fuel boost pump that were discovered during an 
inspection required by an existing AD on a Model 737-300 airplane. We 
issued that AD to detect and correct chafing of the fuel boost pump 
electrical wiring and leakage of fuel into the conduit, and to prevent 
electrical arcing between the wiring and the surrounding conduit, which 
could result in arc-through of the conduit, and consequent fire or 
explosion of the fuel tank.

Relevant Service Information

    Since we issued AD 2007-11-07, Boeing has issued Service Bulletin 
737-28A1263, Revision 2, dated August 10, 2007. We referred to Boeing 
Alert Service Bulletin 737-28A1263, Revision 1, dated March 19, 2007, 
as the appropriate source of service information for accomplishing 
certain actions in AD 2007-11-07. The procedures in Revision 2 of the 
service bulletin are essentially the same as those in Revision 1, with 
several editorial changes such as a revised e-mail address, and the 
addition of references to AD 2007-11-07. Revision 2 also incorporates 
alternative methods of compliance (AMOCs) previously approved for AD 
2007-11-07.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other airplanes of the same type design. For this reason, we 
are issuing this AD to supersede AD 2007-11-07. This new AD retains 
certain requirements of the existing AD. This AD also reduces the 
compliance threshold for certain airplanes.

Interim Action

    We consider this AD interim action. If final action is later 
identified, we might consider further rulemaking then.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD; therefore, providing notice and

[[Page 65448]]

opportunity for public comment before the AD is issued is 
impracticable, and good cause exists to make this AD effective in less 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. However, we invite 
you to send any written data, views, or arguments about this AD. Send 
your comments to an address listed under the ADDRESSES section. Include 
``Docket No. FAA-2007-0211; Directorate Identifier 2007-NM-221-AD'' at 
the beginning of your comments. We specifically invite comments on the 
overall regulatory, economic, environmental, and energy aspects of this 
AD. We will consider all comments received by the closing date and may 
amend this AD because of those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the 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 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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends part 39 of the Federal Aviation Regulations (14 CFR part 
39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-15064 (72 FR 28597, May 22, 2007), corrected at 
72 FR 46559, August 21, 2007, and adding the following new 
airworthiness directive (AD):

2007-24-02 Boeing: Docket No. FAA-2007-0211; Directorate Identifier 
2007-NM-221-AD; Amendment 39-15268.

Effective Date

    (a) This AD becomes effective December 6, 2007.

Affected ADs

    (b) This AD supersedes AD 2007-11-07.

Applicability

    (c) This AD applies to all Boeing Model 737-100, -200, -200C, -
300, -400, and -500 series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report of a fuel tank explosion on a 
Model 727-200F airplane on the ground, and a report of chafed wires 
and a damaged power cable sleeve of a fuel boost pump discovered 
during an inspection on a Model 737-300 airplane. (The fuel boost 
pump installation on certain Model 737 airplanes is almost identical 
to the installation on Model 727 airplanes.) We are issuing this AD 
to detect and correct chafing of the fuel boost pump electrical 
wiring and leakage of fuel into the conduit, and to prevent 
electrical arcing between the wiring and the surrounding conduit, 
which could result in arc-through of the conduit, and consequent 
fire or explosion of the fuel tank.

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.

Certain Requirements of AD 2007-11-07

Inspection and Related Investigative and Corrective Actions

    (f) At the applicable time specified by paragraph (f)(1) or 
(f)(2) of this AD: Do a detailed inspection for damage of the sleeve 
and electrical wire of the fuel boost pump; and, before further 
flight, install a new, smaller-diameter sleeve, and do related 
investigative and corrective actions, as applicable; in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 737-28A1263, Revision 1, dated March 19, 2007; or Boeing 
Service Bulletin 737-28A1263, Revision 2, dated August 10, 2007. 
After the effective date of this AD, Revision 2 must be used. 
Thereafter, repeat the detailed inspection at intervals not to 
exceed 15,000 flight hours.
    (1) For Model 737-100, -200, -300, -400, and -500 series 
airplanes: At the time specified in paragraph (i) or (j) of this AD, 
as applicable.
    (2) For Model 737-200C series airplanes: Within 120 days after 
June 6, 2007 (the effective date of AD 2007-11-07), or within 5,000 
flight hours after the last inspection or repair done in accordance 
with any version of Boeing Alert Service Bulletin 737-28-1120, 
whichever occurs later.

Inspection Report and Disposition of Damaged Parts

    (g) At the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD: Submit a report of the findings (both positive 
and negative) of any inspection required by paragraph (f) of this AD 
and send any damaged parts to the manufacturer, as described in 
Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated March 
19, 2007. The report must include the inspection results, a 
description of any discrepancies found, the airplane serial number, 
and the number of landings and flight hours on the airplane. Under 
the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et 
seq.), the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.
    (1) For any inspection done on or after June 6, 2007: Submit the 
report within 30 days after the inspection.
    (2) For any inspection done before June 6, 2007: Submit the 
report within 30 days after June 6, 2007.

Credit for Actions Done Using Previous Service Information

    (h) Actions accomplished before June 6, 2007, in accordance with 
Boeing Service

[[Page 65449]]

Bulletin 737-28A1263, dated February 19, 2007, are considered 
acceptable for compliance with the corresponding actions specified 
in this AD.

New Requirements of This AD

Previously Required Inspection at New Compliance Times

    (i) For Model 737-100, -200, -300, -400, and -500 series 
airplanes having line numbers 1 through 3072 inclusive: Within 120 
days after the effective date of this AD, or within 5,000 flight 
hours after the last inspection or repair done in accordance with 
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or 
(i)(4) of this AD, whichever occurs later, do the actions specified 
in paragraph (f) of this AD.
    (1) Boeing Alert Service Bulletin 737-28A1120, dated April 24, 
1998, as revised by Notices of Status Change NSC 01, dated May 7, 
1998, NSC 02, dated May 8, 1998, and NSC 03, dated May 9, 1998.
    (2) Boeing Alert Service Bulletin 737-28A1120, Revision 1, dated 
May 28, 1998.
    (3) Boeing Alert Service Bulletin 737-28A1120, Revision 2, dated 
November 26, 1998.
    (4) Boeing Service Bulletin 737-28A1120, Revision 3, dated April 
26, 2001.
    (j) For Model 737-100, -200, -300, -400, and -500 series 
airplanes having line numbers 3073 and subsequent: At the applicable 
time specified in paragraph (j)(1) or (j)(2) of this AD, do the 
actions specified in paragraph (f) of this AD.
    (1) For airplanes on which the inspection or repair specified in 
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or 
(i)(4) of this AD, has been done as of the effective date of this 
AD: Within 120 days after the effective date of this AD or 5,000 
flight hours after the last inspection done in accordance with any 
service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or 
(i)(4) of this AD, whichever occurs later.
    (2) For airplanes on which the inspection or repair specified in 
any service bulletin listed in paragraph (i)(1), (i)(2), (i)(3), or 
(i)(4) of this AD, has not been done as of the effective date of 
this AD: Before the accumulation of 5,000 total flight hours, or 
within 120 days after the effective date of this AD, whichever 
occurs later.

Inspection Report and Disposition of Damaged Parts

    (k) For Model 737-100, -200, -300, -400, and -500 series 
airplanes: At the applicable time specified in paragraph (k)(1) or 
(k)(2) of this AD, submit a report of the findings (both positive 
and negative) of any inspection required by paragraph (i) or (j) of 
this AD and send any damaged parts to the manufacturer, as described 
in Boeing Service Bulletin 737-28A1263, Revision 2, dated August 10, 
2007. The report must include the inspection results, a description 
of any discrepancies found, the airplane serial number, and the 
number of landings and flight hours on the airplane. Under the 
provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), 
the Office of Management and Budget (OMB) has approved the 
information collection requirements contained in this AD and has 
assigned OMB Control Number 2120-0056.
    (1) For any inspection done after the effective date of this AD: 
Submit the report within 30 days after the inspection.
    (2) For any inspection done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(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) AMOCs approved previously in accordance with AD 99-21-15, 
amendment 39-11360, and AD 2007-11-07 are approved as AMOCs for the 
corresponding provisions of this AD.

Material Incorporated by Reference

    (m) You must use applicable Boeing service bulletins specified 
in Table 1 of this AD to perform the actions that are required by 
this AD, unless the AD specifies otherwise.

            Table 1.--All Material Incorporated by Reference
------------------------------------------------------------------------
                                 Revision
       Service Bulletin           level                 Date
------------------------------------------------------------------------
Boeing Alert Service Bulletin            1  March 19, 2007.
 737-28A1263.
Boeing Service Bulletin 737-             2  August 10, 2007.
 28A1263.
------------------------------------------------------------------------

    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Service Bulletin 737-28A1263, 
Revision 2, dated August 10, 2007, in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51.
    (2) On June 6, 2007 (72 FR 28597, May 22, 2007), the Director of 
the Federal Register approved the incorporation by reference of 
Boeing Alert Service Bulletin 737-28A1263, Revision 1, dated March 
19, 2007.
    (3) Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call 202-741-6030, or go to: 
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on November 8, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-22724 Filed 11-20-07; 8:45 am]
BILLING CODE 4910-13-P