Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP Series Airplanes, 49351-49354 [E9-23294]

Download as PDF Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Fokker Services B.V.: Docket No. FAA– 2009–0793; Directorate Identifier 2009– NM–051–AD. Comments Due Date (a) We must receive comments by October 28, 2009. Affected ADs (b) None. CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS Applicability (c) This AD applies to Fokker Model F.28 Mark 0070 and 0100 airplanes, certificated in any category, all serial numbers, if equipped with an ‘‘airstair’’ type door with a passenger door actuator having part number (P/N) A26900–401, A82936–701, A82936–705, R5320, R5320–1, R5320–12, W26900–401, W53200–401, W53200–403, or W53200–405. Subject (d) Air Transport Association (ATA) of America Code 52: Doors. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Several cases have been reported where a passenger door actuator detached from the passenger door. This caused the passenger door to drop to the platform in an uncontrolled manner. VerDate Nov<24>2008 14:31 Sep 25, 2009 Jkt 217001 This condition, if not corrected, could result in injury to persons on the ground and damage to the aircraft. To address this problem, Fokker Services has developed an improved actuator to ensure the proper functioning of the door opening mechanism. For the reason described above, this AD requires the replacement of existing airstair door actuators with improved actuators. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 7,500 flight cycles after the effective date of this AD, replace the affected door actuator with a new or modified unit that has a part number not identified in paragraph (c) of this AD, in accordance with Fokker Service Bulletin SBF100–52–087, dated November 10, 2008. (2) As of 18 months after the effective date of this AD, no person may install on any airplane a door actuator with a part number listed in paragraph (c) of this AD; modification of the actuators in accordance with Fokker Component Service Bulletin R5320–52–011, dated November 10, 2008, changes the part number of the actuator. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2009– PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 49351 0026, dated February 17, 2009; Fokker Service Bulletin SBF100–52–087, dated November 10, 2008; and Fokker Component Service Bulletin R5320–52–011, dated November 10, 2008; for related information. Issued in Renton, Washington, on September 18, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–23299 Filed 9–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0794; Directorate Identifier 2009–NM–035–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747– 400F, 747SR, and 747SP Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for all Boeing Model 747 airplanes. This proposed AD would require a general visual inspection to identify any existing repairs of the upper main sill outer chord of the left and right side main entry door number 1, as applicable; repetitive detailed inspections for cracks in the upper main sill of the door(s); and related investigative and corrective actions, if necessary. This proposed AD would also require repetitive inspections for airplanes on which a certain repair is done, and corrective actions if necessary. This proposed AD results from reports of cracks in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes. We are proposing this AD to detect and correct such cracks, which could result in loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by November 12, 2009. 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. E:\FR\FM\28SEP1.SGM 28SEP1 49352 Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules • 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 proposed 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 or 425–227–1152. 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 proposed 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: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0794; Directorate Identifier 2009–NM–035–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this VerDate Nov<24>2008 14:31 Sep 25, 2009 Jkt 217001 proposed 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 proposed AD. Discussion We have received reports in the main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes. The cracks have been attributed to fatigue. This condition, if not detected and corrected, could result in loss of structural integrity of the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009. The service bulletin describes procedures for a general visual inspection to identify any existing structural repair manual (SRM) repairs of the upper main sill outer chord of the left and right side main entry door number 1, as applicable, repetitive detailed inspections to detect cracks in the upper main sill of the door(s), and related investigative and corrective actions, if necessary. The related investigative action is to remove any existing SRM outer chord repair found and do a detailed inspection for cracks of the upper main sill and corrective actions, if necessary. The corrective actions include: • For airplanes on which any crack is found in the upper main sill outer chord, install an outer chord repair in accordance with Boeing drawing 691U0145; • For airplanes on which any existing SRM outer chord repair is removed, install a new repair in accordance with Boeing drawing 691U0145; • For airplanes on which any crack is found in the frame attachment angles or clips of the upper main sill, replace the cracked angle or clip with a new part; and • For airplanes on which any crack is found in the upper main sill web, contact Boeing for repair instructions. The service bulletin also describes procedures for repetitive after-repair inspections of any upper main sill(s) that has been repaired in accordance with Boeing drawing 691U0145. For airplanes on which any crack is found during the after-repair inspections, the service bulletin specifies contacting Boeing for repair instructions. The compliance time for the initial general visual and detailed inspections PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 is before 9,000 total flight cycles or within 12,000 flight cycles after installation of the Zone 3 modification in accordance with Boeing Service Bulletin 747–53–2272, depending on the configuration of the airplane; or within 1,500 flight cycles after the date on the service bulletin; whichever occurs later. The repetitive interval for the detailed inspection is 6,000 flight cycles. The compliance time for the after-repair inspection is within 15,000 flight cycles after the installation of the repair in accordance with Boeing drawing 691U0145, or within 1,500 flight cycles after the date on the service bulletin, whichever occurs later. The repetitive interval for the after-repair inspection is 3,000 flight cycles. The compliance time for all related investigative and corrective actions is before further flight. FAA’s Determination and Requirements of this Proposed AD We are proposing this AD because we evaluated all relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between the Proposed AD and the Service Bulletin.’’ Differences between the Proposed AD and the Service Bulletin The service bulletin specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: • Using a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization whom we have authorized to make those findings. Where the service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Costs of Compliance We estimate that this proposed AD would affect 165 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this proposed AD. E:\FR\FM\28SEP1.SGM 28SEP1 Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules 49353 TABLE—ESTIMATED COSTS Action Average labor rate per hour Work hours Parts Cost per product Inspection (groups 1, 3) 6 $80 $0 Inspection (groups 2, 4) 3 80 0 $480, per inspection cycle. $240, per inspection cycle. Inspections (g) At the applicable times specified in Table 1 of paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, except as required by paragraphs (j), (k), and (l) of this AD: Do a general visual inspection to identify any existing structural repair manual (SRM) Credit for Inspections Required by AD 2005– 20–30 or AD 2006–05–02 (j) Accomplishing the inspections required by AD 2005–20–30 or AD 2006–05–02, as applicable, is an acceptable method of compliance for the inspections required by paragraph (g) of this AD. For any airplane that has accumulated 22,000 total flight 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. VerDate Nov<24>2008 14:31 Sep 25, 2009 Jkt 217001 Up to 165 ..... Up to $79,200, per inspection cycle. Up to $39,600, per inspection cycle. 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. The Proposed Amendment We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866, 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. Up to 165 ..... Fleet cost repairs of the upper main sill outer chord of the left and right side main entry door number 1, as applicable; a detailed inspection for cracks in the upper main sill of the door(s); and do all related investigative and corrective actions, as applicable; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009. Do all applicable related investigative and corrective actions before further flight. (h) For airplanes identified in paragraphs (h)(1) and (h)(2) of this AD: Repeat the detailed inspection described in paragraph (g) of this AD thereafter at the interval specified in Table 1 of paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, until the outer chord repair specified in drawing 691U0145 is done on the upper main sill, in accordance with the Accomplishment Instructions of the Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009. (1) Airplanes on which no cracking is found and no existing SRM outer chord repair is found during any inspection required by paragraph (g) of this AD. (2) Airplanes on which sill web or frame attachment angles (or clips) are repaired or replaced in accordance with Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, and the drawing 691U0145 outer chord repair is not installed in accordance with Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009. (i) For airplanes on which the outer chord repair specified in drawing 691U0145 has been installed in accordance with Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009: At the applicable times specified in Table 2 of paragraph 1.E. ‘‘Compliance’’ of Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, except as required by paragraph (l) of this AD, do the after-repair inspections and all applicable corrective actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, except as provided by paragraph (k) of this AD. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. Authority for this Rulemaking Regulatory Findings Number of U.S.registered airplanes 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 AD: Boeing: Docket No. FAA–2009–0794; Directorate Identifier 2009–NM–035–AD. Comments Due Date (a) We must receive comments by November 12, 2009. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, 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 main entry door number 1 upper main sill outer chord, along the bend radius of the chord on several airplanes. The Federal Aviation Administration is issuing this AD to detect and correct such cracks, which could result in loss of structural integrity of the airplane. PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\28SEP1.SGM 28SEP1 49354 Federal Register / Vol. 74, No. 186 / Monday, September 28, 2009 / Proposed Rules cycles or more, AD 2005–20–30 requires accomplishing the inspections in accordance with Boeing Service Bulletin 747–53A2349, Revision 2, dated April 3, 2003; and AD 2006–05–02 requires accomplishing the inspections in accordance with Boeing Alert Service Bulletin 747–53A2500, dated December 21, 2004. DEPARTMENT OF THE TREASURY Exceptions to the Service Bulletin RIN 1545–BI44 (k) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Where Boeing Alert Service Bulletin 747–53A2785, dated February 12, 2009, specifies a compliance time ‘‘after the date on this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. Definition of Omission From Gross Income Alternative Methods of Compliance (AMOCs) CPrice-Sewell on DSKGBLS3C1PROD with PROPOSALS (m)(1) The Manager, Seattle (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6437; fax (425) 917–6590. Or, email information to 9-ANM-Seattle-ACOAMOC-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 an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Issued in Renton, Washington, on September 18, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–23294 Filed 9–25–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 14:31 Sep 25, 2009 Jkt 217001 Internal Revenue Service 26 CFR Part 301 [REG–108045–08] AGENCY: Internal Revenue Service (IRS), Treasury. ACTION: Notice of proposed rulemaking by cross-reference to temporary regulations. SUMMARY: This document contains proposed regulations defining an omission from gross income for purposes of the six-year minimum period for assessment of tax attributable to partnership items and the six-year period for assessing tax. The regulations resolve a continuing issue as to whether an overstatement of basis in a sold asset results in an omission from gross income. The regulations will affect any taxpayer who overstates basis in a sold asset creating an omission from gross income exceeding twenty-five percent of the income stated in the return. The text of the temporary regulations published in the Rules and Regulations section of this issue of the Federal Register also serves as the text of these proposed regulations. This document also provides notice of a public hearing on these proposed and temporary regulations. DATES: Written or electronic comments and requests for a public hearing must be received by December 28, 2009. ADDRESSES: Send submissions to: CC:PA:LPD:PR (REG–108045–08), room 5205, Internal Revenue Service, P.O. Box 7604, Ben Franklin Station, Washington, DC 20044. Submissions may be hand delivered Monday through Friday between the hours of 8 a.m. and 4 p.m. to: CC:PA:LPD:PR (REG–108045– 08), Courier’s Desk, Internal Revenue Service, 1111 Constitution Avenue, NW., Washington, DC, or sent electronically via the Federal eRulemaking Portal at https:// www.regulations.gov (IRS REG–108045– 08). FOR FURTHER INFORMATION CONTACT: Concerning the proposed regulations, William A. Heard, III at (202) 622–4570; concerning submissions of comments and requests for a public hearing, Richard.A.Hurst@irscounsel.treas.gov, (202) 622–7180 (not toll-free numbers). SUPPLEMENTARY INFORMATION: PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 Background and Explanation of Provisions Temporary regulations in the Rules and Regulations section of this issue of the Federal Register amend the Procedure and Administration Regulations (26 CFR part 301) relating to sections 6229(c)(2) and 6501(e). The text of those regulations also serves as the text of these proposed regulations. The preamble to the temporary regulations explains the amendments. Special Analyses It has been determined that this notice of proposed rulemaking is not a significant regulatory action as defined in Executive Order 12866. Therefore, a regulatory assessment is not required. It also has been determined that section 553(b) of the Administrative Procedure Act (5 U.S.C. chapter 5) does not apply to these regulations and because these regulations do not impose a collection of information on small entities, the Regulatory Flexibility Act (5 U.S.C. chapter 6) does not apply. Pursuant to section 7805(f) of the Internal Revenue Code, these regulations have been submitted to the Chief Counsel for Advocacy of the Small Business Administration for comment on their impact on small business. Comments and Requests for a Public Hearing Before these proposed regulations are adopted as final regulations, consideration will be given to any written (a signed original and eight (8) copies) or electronic comments that are submitted timely to the IRS. The IRS and the Treasury Department request comments on the substance of the proposed regulations, as well as on the clarity of the proposed rules and how they can be made easier to understand. All public comments will be made available for public inspection and copying. A public hearing will be scheduled if requested in writing by any person that timely submits comments. If a public hearing is scheduled, notice of the date, time, and place for the public hearing will be published in the Federal Register. Drafting Information The principal author of these regulations is William A. Heard III of the Office of the Associate Chief Counsel (Procedure and Administration). List of Subjects in 26 CFR Part 301 Employment taxes, Estate taxes, Excise taxes, Gift taxes, Income taxes, Penalties, Reporting and recordkeeping requirements. E:\FR\FM\28SEP1.SGM 28SEP1

Agencies

[Federal Register Volume 74, Number 186 (Monday, September 28, 2009)]
[Proposed Rules]
[Pages 49351-49354]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-23294]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0794; Directorate Identifier 2009-NM-035-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Boeing Model 747 airplanes. This proposed AD would require a general 
visual inspection to identify any existing repairs of the upper main 
sill outer chord of the left and right side main entry door number 1, 
as applicable; repetitive detailed inspections for cracks in the upper 
main sill of the door(s); and related investigative and corrective 
actions, if necessary. This proposed AD would also require repetitive 
inspections for airplanes on which a certain repair is done, and 
corrective actions if necessary. This proposed AD results from reports 
of cracks in the main entry door number 1 upper main sill outer chord, 
along the bend radius of the chord on several airplanes. We are 
proposing this AD to detect and correct such cracks, which could result 
in loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by November 12, 
2009.

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.

[[Page 49352]]

     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 proposed 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:[sol][sol]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 or 
425-227-1152.

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 proposed 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: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0794; 
Directorate Identifier 2009-NM-035-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    We have received reports in the main entry door number 1 upper main 
sill outer chord, along the bend radius of the chord on several 
airplanes. The cracks have been attributed to fatigue. This condition, 
if not detected and corrected, could result in loss of structural 
integrity of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009. The service bulletin describes procedures for a 
general visual inspection to identify any existing structural repair 
manual (SRM) repairs of the upper main sill outer chord of the left and 
right side main entry door number 1, as applicable, repetitive detailed 
inspections to detect cracks in the upper main sill of the door(s), and 
related investigative and corrective actions, if necessary.
    The related investigative action is to remove any existing SRM 
outer chord repair found and do a detailed inspection for cracks of the 
upper main sill and corrective actions, if necessary.
    The corrective actions include:
     For airplanes on which any crack is found in the upper 
main sill outer chord, install an outer chord repair in accordance with 
Boeing drawing 691U0145;
     For airplanes on which any existing SRM outer chord repair 
is removed, install a new repair in accordance with Boeing drawing 
691U0145;
     For airplanes on which any crack is found in the frame 
attachment angles or clips of the upper main sill, replace the cracked 
angle or clip with a new part; and
     For airplanes on which any crack is found in the upper 
main sill web, contact Boeing for repair instructions.
    The service bulletin also describes procedures for repetitive 
after-repair inspections of any upper main sill(s) that has been 
repaired in accordance with Boeing drawing 691U0145. For airplanes on 
which any crack is found during the after-repair inspections, the 
service bulletin specifies contacting Boeing for repair instructions.
    The compliance time for the initial general visual and detailed 
inspections is before 9,000 total flight cycles or within 12,000 flight 
cycles after installation of the Zone 3 modification in accordance with 
Boeing Service Bulletin 747-53-2272, depending on the configuration of 
the airplane; or within 1,500 flight cycles after the date on the 
service bulletin; whichever occurs later. The repetitive interval for 
the detailed inspection is 6,000 flight cycles. The compliance time for 
the after-repair inspection is within 15,000 flight cycles after the 
installation of the repair in accordance with Boeing drawing 691U0145, 
or within 1,500 flight cycles after the date on the service bulletin, 
whichever occurs later. The repetitive interval for the after-repair 
inspection is 3,000 flight cycles. The compliance time for all related 
investigative and corrective actions is before further flight.

FAA's Determination and Requirements of this Proposed AD

    We are proposing this AD because we evaluated all relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design. 
This proposed AD would require accomplishing the actions specified in 
the service information described previously, except as discussed under 
``Differences Between the Proposed AD and the Service Bulletin.''

Differences between the Proposed AD and the Service Bulletin

    The service bulletin specifies to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions in one of the following ways:
     Using a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.
    Where the service bulletin specifies a compliance time after the 
date on the service bulletin, this AD requires compliance within the 
specified compliance time after the effective date of this AD.

Costs of Compliance

    We estimate that this proposed AD would affect 165 airplanes of 
U.S. registry. The following table provides the estimated costs for 
U.S. operators to comply with this proposed AD.

[[Page 49353]]



                                                                 Table--Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                     Average labor                                             Number of U.S.-
              Action                  Work hours     rate per hour       Parts         Cost per product     registered airplanes         Fleet cost
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspection (groups 1, 3)..........               6             $80              $0  $480, per inspection   Up to 165.............  Up to $79,200, per
                                                                                     cycle.                                         inspection cycle.
Inspection (groups 2, 4)..........               3              80               0  $240, per inspection   Up to 165.............  Up to $39,600, per
                                                                                     cycle.                                         inspection cycle.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866,
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979), and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Boeing: Docket No. FAA-2009-0794; Directorate Identifier 2009-NM-
035-AD.

Comments Due Date

    (a) We must receive comments by November 12, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 
747-400F, 747SR, and 747SP series airplanes, 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 main entry 
door number 1 upper main sill outer chord, along the bend radius of 
the chord on several airplanes. The Federal Aviation Administration 
is issuing this AD to detect and correct such cracks, which could 
result in loss of structural integrity 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.

Inspections

    (g) At the applicable times specified in Table 1 of paragraph 
1.E. ``Compliance'' of Boeing Alert Service Bulletin 747-53A2785, 
dated February 12, 2009, except as required by paragraphs (j), (k), 
and (l) of this AD: Do a general visual inspection to identify any 
existing structural repair manual (SRM) repairs of the upper main 
sill outer chord of the left and right side main entry door number 
1, as applicable; a detailed inspection for cracks in the upper main 
sill of the door(s); and do all related investigative and corrective 
actions, as applicable; in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009. Do all applicable related investigative and 
corrective actions before further flight.
    (h) For airplanes identified in paragraphs (h)(1) and (h)(2) of 
this AD: Repeat the detailed inspection described in paragraph (g) 
of this AD thereafter at the interval specified in Table 1 of 
paragraph 1.E. ``Compliance'' of Boeing Alert Service Bulletin 747-
53A2785, dated February 12, 2009, until the outer chord repair 
specified in drawing 691U0145 is done on the upper main sill, in 
accordance with the Accomplishment Instructions of the Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009.
    (1) Airplanes on which no cracking is found and no existing SRM 
outer chord repair is found during any inspection required by 
paragraph (g) of this AD.
    (2) Airplanes on which sill web or frame attachment angles (or 
clips) are repaired or replaced in accordance with Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009, and the 
drawing 691U0145 outer chord repair is not installed in accordance 
with Boeing Alert Service Bulletin 747-53A2785, dated February 12, 
2009.
    (i) For airplanes on which the outer chord repair specified in 
drawing 691U0145 has been installed in accordance with Boeing Alert 
Service Bulletin 747-53A2785, dated February 12, 2009: At the 
applicable times specified in Table 2 of paragraph 1.E. 
``Compliance'' of Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009, except as required by paragraph (l) of this AD, 
do the after-repair inspections and all applicable corrective 
actions in accordance with the Accomplishment Instructions of Boeing 
Alert Service Bulletin 747-53A2785, dated February 12, 2009, except 
as provided by paragraph (k) of this AD. Repeat the inspections 
thereafter at intervals not to exceed 3,000 flight cycles.

Credit for Inspections Required by AD 2005-20-30 or AD 2006-05-02

    (j) Accomplishing the inspections required by AD 2005-20-30 or 
AD 2006-05-02, as applicable, is an acceptable method of compliance 
for the inspections required by paragraph (g) of this AD. For any 
airplane that has accumulated 22,000 total flight

[[Page 49354]]

cycles or more, AD 2005-20-30 requires accomplishing the inspections 
in accordance with Boeing Service Bulletin 747-53A2349, Revision 2, 
dated April 3, 2003; and AD 2006-05-02 requires accomplishing the 
inspections in accordance with Boeing Alert Service Bulletin 747-
53A2500, dated December 21, 2004.

Exceptions to the Service Bulletin

    (k) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 747-53A2785, dated February 
12, 2009, specifies to contact Boeing for appropriate action: Before 
further flight, repair the crack using a method approved in 
accordance with the procedures specified in paragraph (m) of this 
AD.
    (l) Where Boeing Alert Service Bulletin 747-53A2785, dated 
February 12, 2009, specifies a compliance time ``after the date on 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (m)(1) The Manager, Seattle (ACO), FAA, has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19. Send information to ATTN: Ivan Li, Aerospace 
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 917-6437; fax (425) 917-6590. Or, e-mail 
information 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 an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

    Issued in Renton, Washington, on September 18, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-23294 Filed 9-25-09; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.