Airworthiness Directives; The Boeing Company Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F Series Airplanes, 1339-1342 [2011-188]

Download as PDF Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations PART 301—DOMESTIC QUARANTINE NOTICES Accordingly, we are adopting as a final rule, without change, the interim rule that amended 7 CFR part 301 and that was published at 74 FR 47999– 48001 on September 21, 2009. ■ Done in Washington, DC, this 4th day of January 2011. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2011–227 Filed 1–7–11; 8:45 am] BILLING CODE 3410–34–P DEPARTMENT OF AGRICULTURE Animal and Plant Health Inspection Service 7 CFR Part 301 [Docket No. APHIS–2008–0111] Pine Shoot Beetle; Additions to Quarantined Areas Animal and Plant Health Inspection Service, USDA. ACTION: Affirmation of interim rule as final rule. AGENCY: We are adopting as a final rule, without change, an interim rule that amended the pine shoot beetle (PSB) regulations by adding the entire State of Ohio and counties in Maine and Indiana to the list of quarantined areas following the detection of PSB in those areas. The interim rule was necessary to prevent the spread of PSB, a pest of pine trees, into noninfested areas of the United States. DATES: Effective on January 10, 2011, we are adopting as a final rule the interim rule published at 74 FR 48003–48005 on September 21, 2009. FOR FURTHER INFORMATION CONTACT: Dr. Brendon Reardon, National Program Manager, Emergency and Domestic Programs, PPQ, APHIS, 4700 River Road Unit 26, Riverdale, MD 20737–1231; (301) 734–5705. SUPPLEMENTARY INFORMATION: wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 SUMMARY: Background Pine shoot beetle (PSB) is a destructive forest pest that attacks both managed and natural stands of pine and especially affects weak and dying trees. The beetle has been found in a variety of pine species (Pinus spp.) in the United States. Scotch pine (P. sylvestris) is the pest’s preferred host. PSB has been reported to also occasionally attack other conifers such as fir (Abies spp.) and spruce (Picea spp.) at low levels. VerDate Mar<15>2010 14:40 Jan 07, 2011 Jkt 223001 During ‘‘shoot feeding,’’ young beetles tunnel into the center of pine shoots (usually those from the current year’s growth), causing stunted and distorted growth in host trees. Large infestations of PSB typically kill most of the lateral shoots near the tops of trees. In addition, PSB is a vector of several diseases of pine trees. The regulations in 7 CFR 301.50 through 301.50–10 (referred to below as the regulations) restrict the interstate movement of certain regulated articles from quarantined areas in order to prevent the spread of PSB into noninfested areas of the United States. In an interim rule 1 effective and published in the Federal Register on September 21, 2009 (74 FR 48003– 48005, Docket No. APHIS–2008–0111), we amended the regulations by adding the entire State of Ohio and counties in Maine and Indiana to the list of quarantined areas in § 301.50–3(c). Comments on the interim rule were required to be received on or before November 20, 2009. We did not receive any comments. Therefore, for the reasons given in the interim rule, we are adopting the interim rule as a final rule without change. This action also affirms the information contained in the interim rule concerning Executive Order 12866 and the Regulatory Flexibility Act, Executive Orders 12372 and 12988, and the Paperwork Reduction Act. Further, for this action, the Office of Management and Budget has waived its review under Executive Order 12866. List of Subjects in 7 CFR Part 301 Agricultural commodities, Plant diseases and pests, Quarantine, Reporting and recordkeeping requirements, Transportation. PART 301—DOMESTIC QUARANTINE NOTICES Accordingly, we are adopting as a final rule, without change, the interim rule that amended 7 CFR part 301 and that was published at 74 FR 48003– 48005, on September 21, 2009. ■ Done in Washington, DC, this 4th day of January 2011. Kevin Shea, Acting Administrator, Animal and Plant Health Inspection Service. [FR Doc. 2011–230 Filed 1–7–11; 8:45 am] BILLING CODE 3410–34–P 1 To view the interim rule, go to https:// www.regulations.gov/fdmspublic/component/ main?main=DocketDetail&d=APHIS-2008-0111. PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 1339 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0646; Directorate Identifier 2009–NM–223–AD; Amendment 39–16558; AD 2011–01–05] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Model 727, 727C, 727–100, 727–100C, 727–200, and 727–200F Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive detailed inspections of the aft pressure bulkhead web for cracking, and repair if necessary. For certain airplanes, this AD also provides for an optional preventative modification of the aft pressure bulkhead web, which would terminate certain repetitive detailed inspections. This AD was prompted by reports of cracks in the aft pressure bulkhead web. We are issuing this AD to detect and correct cracking in the aft pressure bulkhead web, which could adversely affect the structural integrity of the airplane, resulting in difficulty maintaining cabin pressurization or rapid decompression of the airplane. DATES: This AD is effective February 14, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of February 14, 2011. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. SUMMARY: 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 E:\FR\FM\10JAR1.SGM 10JAR1 1340 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6577; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to the specified products. That NPRM was published in the Federal Register on July 1, 2010 (75 FR 38066). That NPRM proposed to require repetitive detailed inspections of the aft pressure bulkhead web for cracking, and repair if necessary. For certain airplanes, that NPRM also proposed an optional preventative modification of the aft pressure bulkhead web, which would terminate certain repetitive detailed inspections. Comments We gave the public the opportunity to participate in developing this AD. The following paragraphs present the comments received on the proposal and the FAA’s response to each comment. Request To Rephrase Unsafe Condition Statement in the AD Boeing requested that we change the second sentence of paragraph (e) of the AD to state that the FAA ‘‘is issuing this AD to detect and repair cracking, or to modify structure to prevent cracking, in the aft pressure bulkhead web * * *’’ The commenter stated that the original paragraph specified that the AD is being issued ‘‘to prevent cracking,’’ whereas the AD provides modification instructions to prevent cracking, as well as instructions to repair cracking, and the requested language is more correct. We partially agree with the commenter’s request. We agree to change the AD to say ‘‘detect and correct cracking’’ because the AD provides those instructions, and we have changed paragraph (e) accordingly. We disagree with including ‘‘modify structure to prevent cracking’’ because the AD does not mandate the preventive modification. The modification to prevent cracking is available as an option in the AD and in Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009, the service information referenced in the NPRM; we have made no further change to the AD in this regard. Request To Remove Description From Paragraph (g) of the AD Boeing requested that we remove ‘‘* * * in the area around the hydraulic line support bracket on the left side * * *’’ from paragraph (g) of the AD. The commenter stated that airplanes in Group 1, Configuration 2, do not have that hydraulic bracket installed, and therefore cannot be inspected ‘‘around the bracket.’’ Boeing stated further that the service bulletin specifies an inspection in the entire bay of the web, and the requested change would cover all the subject airplanes and prevent confusion. We agree with the commenter’s request, for the reasons given, and we have changed paragraph (g) of the AD accordingly. Request To Correct Table Reference in Paragraph (g)(2) of the AD Boeing requested that in paragraph (g)(2) of the NPRM we refer only to Table 2 of paragraph 1.E., ‘‘Compliance,’’ in Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009, for the applicable compliance time. The commenter stated that paragraph (g)(2) of the AD covers only airplanes of Group 1, Configuration 2, which are addressed only in Table 2 of paragraph 1.E. of that service bulletin. We agree with the commenter’s request, for the reasons given, and we have changed paragraph (g)(2) of the AD accordingly. We have also changed paragraph (g)(1)(ii) of this AD to only refer to Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. Clarification of Terminating Action We have clarified that for Group 1, Configuration 1 airplanes, and Group 2 airplanes, as identified in Boeing Special Attention Service Bulletin 727– 53–0232, dated September 23, 2009, doing the repair specified in paragraph (h) of the AD terminates the repetitive inspections required by paragraph (g)(1)(ii) of the AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD affects 243 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. TABLE—ESTIMATED COSTS Action Work hours wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 Detailed inspection, per inspection cycle. Preventative modification Average labor rate per hour Parts Cost per product $85, per inspection cycle. $340 ................. 1 $85 None ................. 4 85 Negligible 1 ........ Number of U.S.registered airplanes Fleet cost 243 ................... $20,655, per inspection cycle. Up to 243 .......... Up to $82,620. 1 The cost of material for the modification would depend on the size and location of the repair; the materials necessary for the modification are standard shop materials that would be provided out of the operator’s stock. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, VerDate Mar<15>2010 14:40 Jan 07, 2011 Jkt 223001 section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 E:\FR\FM\10JAR1.SGM 10JAR1 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations 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 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 DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) 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. 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 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 ■ 2011–01–05 The Boeing Company: Amendment 39–16558; Docket No. FAA–2010–0646; Directorate Identifier 2009–NM–223–AD. Effective Date (a) This AD is effective February 14, 2011. Affected ADs (b) None. VerDate Mar<15>2010 14:40 Jan 07, 2011 Jkt 223001 Applicability (c) This AD applies to all The Boeing Company Model 727, 727C, 727–100, 727– 100C, 727–200, and 727–200F series airplanes, certificated in any category. Subject (d) Air Transport Association (ATA) of America Code 53: Fuselage. Unsafe Condition (e) This AD results from reports of cracks in the aft pressure bulkhead web. The Federal Aviation Administration is issuing this AD to detect and correct cracking in the aft pressure bulkhead web, which could adversely affect the structural integrity of the airplane, resulting in difficulty maintaining cabin pressurization or rapid decompression of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections and Corrective Actions (g) At the applicable initial compliance time specified in Tables 1 and 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009; except as provided by paragraph (j) of this AD: Perform a detailed inspection for cracking on the aft side of the aft pressure bulkhead web between water line (WL) 217 to WL 230, and buttock line (BL) 48 left to BL 66 left. Do the inspection in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. (1) For Group 1, Configuration 1 airplanes, and Group 2 airplanes, as identified in Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009: If no cracking is found during the inspection required by paragraph (g) of this AD, do the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. (i) Accomplish the preventative modification specified in Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009, before further flight. (ii) Repeat the detailed inspection at the applicable interval specified in Table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. Accomplishing the preventative modification specified in paragraph (g)(1)(i) of this AD terminates the repetitive inspections required by this paragraph. (2) For Group 1, Configuration 2 airplanes, as identified in Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009: If no cracking is found during the inspection required by paragraph (g) of this AD, repeat the detailed inspection at the applicable interval specified in Table PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 1341 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009. Note 1: The damage tolerance inspections specified in Table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009, may be used in support of compliance with section 121.1109(c)(2) or 129.109(c)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(c)(2)). (h) If any crack is found during any inspection required by paragraph (g) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009; except as provided by paragraph (i) of this AD. For Group 1, Configuration 1 airplanes, and Group 2 airplanes, as identified in Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009: Accomplishing this repair terminates the repetitive inspections required by paragraph (g)(1)(ii) of this AD. (i) If any cracking is found during any inspection required by this AD, and Boeing Special Attention Service Bulletin 727–53– 0232, dated September 23, 2009, specifies to contact Boeing for appropriate action: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Where Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009, specifies a compliance time after the date on that service bulletin, this AD requires compliance within the specified compliance time after 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 using the procedures found in 14 CFR 39.19. Send information to ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6577; fax (425) 917–6590. Information may be e-mailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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 principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that 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. E:\FR\FM\10JAR1.SGM 10JAR1 1342 Federal Register / Vol. 76, No. 6 / Monday, January 10, 2011 / Rules and Regulations Related Information (l) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6577; fax (425) 917–6590. Material Incorporated by Reference (m) You must use Boeing Special Attention Service Bulletin 727–53–0232, dated September 23, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766– 5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202–741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–188 Filed 1–7–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 [Docket No. FAA–2007–28435 Directorate Identifier 2007–CE–054–AD; Amendment 39–16556; AD 2011–01–03] wwoods2 on DSK1DXX6B1PROD with RULES_PART 1 RIN 2120–AA64 Airworthiness Directives; GROB– WERKE GMBH & CO KG Models G102 ASTIR CS, G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III Gliders Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. VerDate Mar<15>2010 14:40 Jan 07, 2011 Jkt 223001 As a result of the replacement action of the G 103 TWIN ASTIR spar spigot assemblies, the Gliding Federation of Australia issued a directive to inspect the similar main spigots of single-seater sailplanes. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 14, 2011. On February 14, 2011, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. For service information identified in this AD, contact Grob Aircraft; Lettenbachstr. 9; TussenhausenMattsies; Head of Customer Service & Support, Germany; telephone: +49 (0) 8268 998 139; fax: +49 (0) 8268 998 200; E-mail: productsupport@grobaircraft.com; Web site: https://www.grobaircraft.com. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329– 4148. FOR FURTHER INFORMATION CONTACT ONE OF THE FOLLOWING: Federal Aviation Administration AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: • Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090. • Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4130; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion History of AD Actions When the State of Design issues MCAI against a product that is certificated for operation in the United States, the FAA PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 evaluates this information and either issues a corresponding U.S. AD or completes a no action required (NAR) form. In 1988, the FAA’s Brussels, Belgium office evaluated MCAIs. When the Brussels office determined an AD was necessary, the corresponding Directorate issued an AD for the product. NAR forms were completed by the Brussels office. When a NAR form was completed, the Directorates did not always receive a copy since they were not required to take action. The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, issued AD 88–176 Grob, dated August 15, 1988, to apply to the GROB– WERKE GMBH & CO KG G103 twin-seat gliders. That AD required inspection and replacement of the spar spigot assembly to prevent fatigue failure of the spigot. The FAA issued AD 90–02– 09 (55 FR 269, January 4, 1990), effective February 5, 1990, to mandate replacement of the spigot assembly for the G103 twin-seat versions of the glider. The LBA issued 91–5/2 Grob, dated February 1, 1991, to apply to the GROB– WERKE GMBH & CO KG G102 singleseat gliders. The MCAI states: As a result of the replacement action of the G 103 TWIN ASTIR spar spigot assemblies, the Gliding Federation of Australia issued a directive to inspect the similar main spigots of single-seater sailplanes. The MCAI requires you to inspect the wing main spigot assembly before the next flight and replace it on the G102 single-seat gliders. You may obtain further information by examining the MCAI in the AD docket. The FAA inadvertently did not issue an AD on the single-seat versions at the time the LBA issued AD 91–5/2 Grob. The FAA finds no AD or NAR information to correspond with German AD 91–5/2 Grob from that time period. In 1997/1998, the responsibility to evaluate MCAIs transferred from Brussels to the Directorates. The Directorates assimilated all of the Brussels information into the Directorate information, identifying if ADs were issued, if NAR forms were completed, or if neither action was taken. During this time, the Small Airplane Directorate issued a total of 310 AD actions in fiscal year (FY) 1998. This was an increase of 79 percent over the 173 total actions issued in FY–97, and a 121 percent increase over the 140 total actions issued in FY–96. This workload increase contributed to the FAA not identifying the German AD 91– 5/2 Grob as an item without a U.S. AD or NAR correspondence associated with it. E:\FR\FM\10JAR1.SGM 10JAR1

Agencies

[Federal Register Volume 76, Number 6 (Monday, January 10, 2011)]
[Rules and Regulations]
[Pages 1339-1342]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-188]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0646; Directorate Identifier 2009-NM-223-AD; 
Amendment 39-16558; AD 2011-01-05]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 727, 727C, 
727-100, 727-100C, 727-200, and 727-200F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD requires repetitive detailed inspections 
of the aft pressure bulkhead web for cracking, and repair if necessary. 
For certain airplanes, this AD also provides for an optional 
preventative modification of the aft pressure bulkhead web, which would 
terminate certain repetitive detailed inspections. This AD was prompted 
by reports of cracks in the aft pressure bulkhead web. We are issuing 
this AD to detect and correct cracking in the aft pressure bulkhead 
web, which could adversely affect the structural integrity of the 
airplane, resulting in difficulty maintaining cabin pressurization or 
rapid decompression of the airplane.

DATES: This AD is effective February 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of February 14, 
2011.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; 
Internet https://www.myboeingfleet.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information 
on the availability of this material at the FAA, call 425-227-1221.

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

[[Page 1340]]

Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The address for the Docket Office (phone: 800-647-5527) is Document 
Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6577; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
the specified products. That NPRM was published in the Federal Register 
on July 1, 2010 (75 FR 38066). That NPRM proposed to require repetitive 
detailed inspections of the aft pressure bulkhead web for cracking, and 
repair if necessary. For certain airplanes, that NPRM also proposed an 
optional preventative modification of the aft pressure bulkhead web, 
which would terminate certain repetitive detailed inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following paragraphs present the comments received on the 
proposal and the FAA's response to each comment.

Request To Rephrase Unsafe Condition Statement in the AD

    Boeing requested that we change the second sentence of paragraph 
(e) of the AD to state that the FAA ``is issuing this AD to detect and 
repair cracking, or to modify structure to prevent cracking, in the aft 
pressure bulkhead web * * *'' The commenter stated that the original 
paragraph specified that the AD is being issued ``to prevent 
cracking,'' whereas the AD provides modification instructions to 
prevent cracking, as well as instructions to repair cracking, and the 
requested language is more correct.
    We partially agree with the commenter's request. We agree to change 
the AD to say ``detect and correct cracking'' because the AD provides 
those instructions, and we have changed paragraph (e) accordingly. We 
disagree with including ``modify structure to prevent cracking'' 
because the AD does not mandate the preventive modification. The 
modification to prevent cracking is available as an option in the AD 
and in Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009, the service information referenced in the NPRM; we 
have made no further change to the AD in this regard.

Request To Remove Description From Paragraph (g) of the AD

    Boeing requested that we remove ``* * * in the area around the 
hydraulic line support bracket on the left side * * *'' from paragraph 
(g) of the AD. The commenter stated that airplanes in Group 1, 
Configuration 2, do not have that hydraulic bracket installed, and 
therefore cannot be inspected ``around the bracket.'' Boeing stated 
further that the service bulletin specifies an inspection in the entire 
bay of the web, and the requested change would cover all the subject 
airplanes and prevent confusion.
    We agree with the commenter's request, for the reasons given, and 
we have changed paragraph (g) of the AD accordingly.

Request To Correct Table Reference in Paragraph (g)(2) of the AD

    Boeing requested that in paragraph (g)(2) of the NPRM we refer only 
to Table 2 of paragraph 1.E., ``Compliance,'' in Boeing Special 
Attention Service Bulletin 727-53-0232, dated September 23, 2009, for 
the applicable compliance time. The commenter stated that paragraph 
(g)(2) of the AD covers only airplanes of Group 1, Configuration 2, 
which are addressed only in Table 2 of paragraph 1.E. of that service 
bulletin.
    We agree with the commenter's request, for the reasons given, and 
we have changed paragraph (g)(2) of the AD accordingly. We have also 
changed paragraph (g)(1)(ii) of this AD to only refer to Table 1 of 
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009.

Clarification of Terminating Action

    We have clarified that for Group 1, Configuration 1 airplanes, and 
Group 2 airplanes, as identified in Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009, doing the repair 
specified in paragraph (h) of the AD terminates the repetitive 
inspections required by paragraph (g)(1)(ii) of the AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 243 airplanes of U.S. registry. 
The following table provides the estimated costs for U.S. operators to 
comply with this AD.

                                                                                     Table--Estimated Costs
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
                                                    Average
               Action                 Work hours   labor rate             Parts                   Cost per product        Number of U.S.- registered                  Fleet cost
                                                    per hour                                                                      airplanes
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
Detailed inspection, per inspection            1          $85  None.......................  $85, per inspection cycle..  243........................  $20,655, per inspection cycle.
 cycle.
Preventative modification..........            4           85  Negligible \1\.............  $340.......................  Up to 243..................  Up to $82,620.
------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ The cost of material for the modification would depend on the size and location of the repair; the materials necessary for the modification are standard shop materials that would be
  provided out of the operator's stock.

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

[[Page 1341]]

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

    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 DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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

2011-01-05 The Boeing Company: Amendment 39-16558; Docket No. FAA-
2010-0646; Directorate Identifier 2009-NM-223-AD.

Effective Date

    (a) This AD is effective February 14, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all The Boeing Company Model 727, 727C, 
727-100, 727-100C, 727-200, and 727-200F series airplanes, 
certificated in any category.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Unsafe Condition

    (e) This AD results from reports of cracks in the aft pressure 
bulkhead web. The Federal Aviation Administration is issuing this AD 
to detect and correct cracking in the aft pressure bulkhead web, 
which could adversely affect the structural integrity of the 
airplane, resulting in difficulty maintaining cabin pressurization 
or rapid decompression of the airplane.

Compliance

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

Repetitive Inspections and Corrective Actions

    (g) At the applicable initial compliance time specified in 
Tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Special 
Attention Service Bulletin 727-53-0232, dated September 23, 2009; 
except as provided by paragraph (j) of this AD: Perform a detailed 
inspection for cracking on the aft side of the aft pressure bulkhead 
web between water line (WL) 217 to WL 230, and buttock line (BL) 48 
left to BL 66 left. Do the inspection in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009.
    (1) For Group 1, Configuration 1 airplanes, and Group 2 
airplanes, as identified in Boeing Special Attention Service 
Bulletin 727-53-0232, dated September 23, 2009: If no cracking is 
found during the inspection required by paragraph (g) of this AD, do 
the actions specified in paragraph (g)(1)(i) or (g)(1)(ii) of this 
AD in accordance with the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 727-53-0232, dated September 23, 
2009.
    (i) Accomplish the preventative modification specified in Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 727-53-0232, dated September 23, 2009, before 
further flight.
    (ii) Repeat the detailed inspection at the applicable interval 
specified in Table 1 of paragraph 1.E., ``Compliance,'' of Boeing 
Special Attention Service Bulletin 727-53-0232, dated September 23, 
2009. Accomplishing the preventative modification specified in 
paragraph (g)(1)(i) of this AD terminates the repetitive inspections 
required by this paragraph.
    (2) For Group 1, Configuration 2 airplanes, as identified in 
Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009: If no cracking is found during the inspection 
required by paragraph (g) of this AD, repeat the detailed inspection 
at the applicable interval specified in Table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Special Attention Service Bulletin 727-53-
0232, dated September 23, 2009.

    Note 1:  The damage tolerance inspections specified in Table 3 
of paragraph 1.E., ``Compliance,'' of Boeing Special Attention 
Service Bulletin 727-53-0232, dated September 23, 2009, may be used 
in support of compliance with section 121.1109(c)(2) or 
129.109(c)(2) of the Federal Aviation Regulations (14 CFR 
121.1109(c)(2) or 14 CFR 129.109(c)(2)).

    (h) If any crack is found during any inspection required by 
paragraph (g) of this AD, before further flight, repair in 
accordance with the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 727-53-0232, dated September 23, 2009; 
except as provided by paragraph (i) of this AD. For Group 1, 
Configuration 1 airplanes, and Group 2 airplanes, as identified in 
Boeing Special Attention Service Bulletin 727-53-0232, dated 
September 23, 2009: Accomplishing this repair terminates the 
repetitive inspections required by paragraph (g)(1)(ii) of this AD.
    (i) If any cracking is found during any inspection required by 
this AD, and Boeing Special Attention Service Bulletin 727-53-0232, 
dated September 23, 2009, specifies to contact Boeing for 
appropriate action: Before further flight, repair the cracking using 
a method approved in accordance with the procedures specified in 
paragraph (k) of this AD.
    (j) Where Boeing Special Attention Service Bulletin 727-53-0232, 
dated September 23, 2009, specifies a compliance time after the date 
on that service bulletin, this AD requires compliance within the 
specified compliance time after 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 
using the procedures found in 14 CFR 39.19. Send information to 
ATTN: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6577; fax (425) 
917-6590. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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 principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (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 the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that 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.

[[Page 1342]]

Related Information

    (l) For more information about this AD, contact Berhane Alazar, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6577; fax (425) 917-6590.

Material Incorporated by Reference

    (m) You must use Boeing Special Attention Service Bulletin 727-
53-0232, dated September 23, 2009, to do the actions required by 
this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-188 Filed 1-7-11; 8:45 am]
BILLING CODE 4910-13-P

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