Airworthiness Directives; Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D Series Airplanes, 14367-14370 [06-2677]

Download as PDF Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations 14367 TABLE 1.—EMBRAER 170 AMM MAINTENANCE TASKS AMM chapter Task Nos. Date Title 27–11–03 .... 27–41–01 .... 27–11–03–710–801–A, 27–11–03–720–801–A ....... 27–41–01–210–801–A, 27–41–01–220–801–A, 27– 41–01–220–802–A. 27–81–01–710–801–A .............................................. January 25, 2005 .... January 25, 2005 .... Aileron Control Cable–Adjustment/Test. Horizontal Stabilizer Trim Actuator—Inspection/ Check. Slat Actuator—Adjustment/Test. 27–81–01 .... January 25, 2005 .... Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (g)(1) The Manager, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Federal Aviation Administration Related Information (h) Brazilian airworthiness directive 2005– 03–02, effective April 20, 2005, also addresses the subject of this AD. Material Incorporated by Reference cprice-sewell on PROD1PC70 with RULES (i) You must use EMBRAER Temporary Revision 1–3 of the EMBRAER 170 Maintenance Review Board Report MRB– 1621, dated December 27, 2004, to the EMBRAER 170 Airplane Maintenance Manual, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), P.O. Box 343—CEP 12.225, Sao Jose dos Campos—SP, Brazil, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 10, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2675 Filed 3–21–06; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:10 Mar 21, 2006 Jkt 208001 14 CFR Part 39 [Docket No. FAA–2005–22383; Directorate Identifier 2005–NM–102–AD; Amendment 39–14520; AD 2006–06–11] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100B SUD, 747–200B, 747– 300, 747–400, and 747–400D Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747–100B SUD, 747–300, 747–400, and 747–400D series airplanes; and Model 747–200B series airplanes having a stretched upper deck. This AD requires repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and performing related investigative and corrective actions if necessary. This AD results from new reports of severed tension ties, as well as numerous reports of cracked tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression of the airplane. DATES: This AD becomes effective April 26, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 26, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Boeing Model 747– 100B SUD, 747–300, 747–400, and 747– 400D series airplanes; and Model 747– 200B series airplanes having a stretched upper deck (SUD). That NPRM was published in the Federal Register on September 12, 2005 (70 FR 53743). That NPRM proposed to require repetitively inspecting for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and related investigative and corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Discuss Special Freighters The Boeing Company (hereafter referred to in this AD as ‘‘Boeing’’) requests that we revise the Discussion section of the proposed AD to refer to Boeing Model 747–200B(SUD)SF, 747– 300SF, and 747–400SF airplanes. Boeing notes that the Discussion section mentions Boeing 747–200B series airplanes modified under a Boeing- E:\FR\FM\22MRR1.SGM 22MRR1 14368 Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations owned supplemental type certificate (STC) to include a SUD, but doesn’t mention STCs and service bulletins related to converting airplanes into a special freighter configuration. Boeing requests that we add a paragraph to the Discussion section stating that certain ‘‘Boeing Model 747–200B(SUD), 747– 300, and 747–400 series airplanes’’ have been modified to a special freighter configuration and are subject to the identified unsafe condition for the tension ties and frames at body stations (BS) 1120 through 1220 only. Boeing contends that tension ties and frames at BS 880 through 1100 on the airplanes configured as special freighters are more robust and are not subject to the unsafe condition. Boeing states that adding such a paragraph would clarify that special freighters are affected by the AD, but that tension ties and frames at BS 880 through 1100 are not subject to the AD. We agree that a special freighter that is converted from a Boeing 747–200B series airplane having a SUD or from a Boeing 747–300 or –400 series airplane is subject to the unsafe condition addressed by this AD. These airplanes are already included in the applicability of this AD. However, we do not agree with Boeing’s request to refer to tension ties and frames at BS 880 through 1100 on the airplanes converted to special freighters because we have not indicated that the tension ties and frames in this area are subject to the AD. The Discussion section of the proposed AD is not restated in the final rule, so we have made no change with regard to Boeing’s request. Request To Clarify Effect on Other ADs Boeing also requests that we clarify paragraph (b) of the proposed AD to state that, for special freighters that are converted from a Boeing 747–200B series airplane having a SUD or from a Boeing 747–300 or –400 series airplane, the inspections in this AD will not terminate the inspections of structural significant item (SSI) F–19A of Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document (SSID),’’ Revision G, dated December 2000 (hereafter referred to in this AD as ‘‘the SSID’’) for BS 880 through 1100. We agree that this AD does not terminate the inspections of SSI F–19A for BS 880 through 1100. As we stated previously, tension ties and frames in BS 880 through 1100 are not subject to this AD. For clarification, we have revised paragraph (b) of this AD to state that the provisions of that paragraph apply only to areas inspected in accordance with this AD. Request To Clarify Compliance Times Boeing also requests that we revise paragraph (f)(1) of the proposed AD to state that the provision in that paragraph applies only to airplanes identified in Boeing Alert Service Bulletin 747–53A2507. Boeing states that, without this clarification, operators may question whether paragraph (f)(1) applies to all airplanes versus all airplanes specified in Boeing Alert Service Bulletin 747–53A2507. We do not agree with Boeing’s request to clarify the compliance times. Paragraph (f) of this AD refers to paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2507 as the source for compliance times, ‘‘except as provided by paragraphs (f)(1), (f)(2), and (f)(3) of this AD.’’ The compliance times in that service bulletin are also summarized in the preamble of the NPRM. We explained in the preamble of the NPRM, under the heading ‘‘Clarification of Compliance Time for Stage 1 Inspections,’’ that this AD applies to certain airplanes not subject to the inspection in Boeing Service Bulletin 747–53–2483. Paragraph (f)(1) is intended to clarify the applicable compliance time for the Stage 1 inspections for these airplanes. We find that no further clarification of the compliance times is needed. Request To Correct Typographical Error Boeing also requests that we revise paragraph (c) of the proposed AD to refer to Model 747–200B series airplanes instead of ‘‘Model 747–200 series airplanes.’’ We agree. A typographical error resulted in the omission of the letter ‘‘B’’ from the model. We have revised paragraph (c) of this AD accordingly. Clarification of Applicability The proposed AD specified that the actions therein would be applicable to ‘‘Boeing Model 747–100B SUD, 747– 300, 747–400, and 747–400D series airplanes; and Model 747–200[B] series airplanes having a stretched upper deck; certificated in any category; as identified in Boeing Alert Service Bulletin 747–53A2507, dated April 21, 2005.’’ The current effectivity listing in the service bulletin includes airplanes up to and including line number 1358. However, the service bulletin also specifies that airplanes after line number 1358 are affected. Therefore, for clarification, we have revised this AD to apply to all airplanes of the affected models. Clarification of Alternative Method of Compliance (AMOC) Paragraph We have revised this action to clarify the appropriate procedure for notifying the principal inspector before using any approved AMOC on any airplane to which the AMOC applies. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Interim Action We consider this AD interim action. The manufacturer is currently developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, and available, we may consider additional rulemaking. Costs of Compliance There are about 622 airplanes of the affected design in the worldwide fleet. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS cprice-sewell on PROD1PC70 with RULES Action Stage 1 Inspection per inspection cycle.1 VerDate Aug<31>2005 15:10 Mar 21, 2006 Average labor rate per hour Work hours 19 Jkt 208001 PO 00000 $65 Frm 00012 Cost per airplane Number of U.S.registered airplanes $1,235, per inspection cycle ..... Fmt 4700 Sfmt 4700 E:\FR\FM\22MRR1.SGM 76 Fleet cost $93,860, per inspection cycle.1 22MRR1 Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations 14369 ESTIMATED COSTS—Continued Stage 2 Inspection, per inspection cycle. 1 Completing Average labor rate per hour Work hours Action 83 $5,395, per inspection cycle ..... 76 Fleet cost $410,020, per inspection cycle. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 15:10 Mar 21, 2006 Jkt 208001 Compliance Adoption of the Amendment 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. cprice-sewell on PROD1PC70 with RULES Number of U.S.registered airplanes the initial Stage 2 inspection ends the repetitive Stage 1 inspections. Authority for This Rulemaking VerDate Aug<31>2005 65 Cost per airplane Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections and Corrective Actions Applicability (c) This AD applies to all Boeing Model 747–100B SUD, 747–300, 747–400, and 747– 400D series airplanes; and Model 747–200B series airplanes having a stretched upper deck; certificated in any category. (f) Do repetitive detailed and high frequency eddy current inspections, as applicable, for cracking or discrepancies of the fasteners in the tension ties, shear webs, and frames at body stations 1120 through 1220, and related investigative and corrective actions as applicable, by doing all actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2507, dated April 21, 2005, except as provided by paragraphs (g) and (h) of this AD. Do the initial and repetitive Stage 1 and Stage 2 inspections at the applicable times specified in Paragraph 1.E., ‘‘Compliance,’’ of the service bulletin, except as provided by paragraphs (f)(1), (f)(2), and (f)(3) of this AD. Any applicable investigative and corrective actions must be done before further flight. Doing the initial Stage 2 inspection ends the repetitive Stage 1 inspections. (1) For any airplane not identified in and subject to inspections in accordance with Boeing Service Bulletin 747–53–2483: Do the initial Stage 1 inspection in accordance with Boeing Alert Service Bulletin 747–53A2507 before the accumulation of 8,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later. (2) Where Paragraph 1.E., ‘‘Compliance,’’ of the service bulletin specifies a compliance time relative to the original issue date of the service bulletin, this AD requires compliance before the specified compliance time after the effective date of this AD. (3) For any airplane that reaches the applicable compliance time for the initial Stage 2 inspection (as specified in Table 1, Compliance Recommendations, under paragraph 1.E. of the service bulletin) before reaching the applicable compliance time for the initial Stage 1 inspection: Doing the initial Stage 2 inspection eliminates the need to do the Stage 1 inspection. Unsafe Condition (d) This AD results from new reports of severed tension ties, as well as numerous reports of cracked tension ties, broken fasteners, and cracks in the frame, shear web, and shear ties adjacent to tension ties for the upper deck. We are issuing this AD to detect and correct cracking of the tension ties, shear webs, and frames of the upper deck, which could result in rapid decompression of the airplane. Exception to Corrective Action Instructions (g) If any discrepancy; including but not limited to cracking, or broken, loose, or missing fasteners; is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2507, dated April 21, 2005, specifies to contact Boeing for appropriate action: Before further flight, repair the discrepancy using a method approved in accordance with the procedures specified in paragraph (i) of this AD. 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): I 2006–06–11 Boeing: Amendment 39–14520. Docket No. FAA–2005–22383; Directorate Identifier 2005–NM–102–AD. Effective Date (a) This AD becomes effective April 26, 2006. Affected ADs (b) For the areas inspected in accordance with this AD, accomplishing the requirements of paragraph (f) of this AD terminates the corresponding inspection requirements for the upper deck tension ties as required by paragraphs (c) and (d) of AD 2004–07–22, amendment 39–13566, as those paragraphs apply to inspections of structural significant item (SSI) F–19A, as identified in Boeing Document No. D6–35022, ‘‘Supplemental Structural Inspection Document,’’ Revision G, dated December 2000. All other requirements of AD 2004–07– 22 continue to apply. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 E:\FR\FM\22MRR1.SGM 22MRR1 14370 Federal Register / Vol. 71, No. 55 / Wednesday, March 22, 2006 / Rules and Regulations No Reporting Requirement DEPARTMENT OF TRANSPORTATION (h) Although Boeing Alert Service Bulletin 747–53A2507, dated April 21, 2005, specifies reporting inspection findings to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (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. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 747–53A2507, dated April 21, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to http://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 9, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–2677 Filed 3–21–06; 8:45 am] cprice-sewell on PROD1PC70 with RULES BILLING CODE 4910–13–P VerDate Aug<31>2005 15:10 Mar 21, 2006 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22426; Directorate Identifier 2005–NM–105–AD; Amendment 39–14519; AD 2006–06–10] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747–400D, and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 747–100, 747–100B, 747– 100B SUD, 747–200B, 747–200C, 747– 300, 747–400, 747–400D, and 747SR series airplanes. This AD requires a onetime inspection to determine whether any steel doubler (small or large) is installed at the lower forward and upper aft corners of the fuselage cutout at main entry doors (MEDs) number 3. Depending on the results of this inspection, this AD also requires repetitive inspections for cracks of the skin, bearstrap, and small steel doubler (if installed) at the applicable corner or corners of the fuselage cutouts, and related investigative/corrective actions if necessary. This AD also provides the optional terminating action for the repetitive inspections of installing a large steel doubler at the affected corners. This AD results from reports of cracks in the skin and bearstrap at the upper aft corner and at the lower forward corner of the fuselage cutout at MEDs number 3. We are issuing this AD to detect and correct cracks in the skin, bearstrap, and small steel doubler (if installed), which could propagate and result in rapid decompression of the airplane. This AD becomes effective April 26, 2006. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 26, 2006. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, DATES: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Washington 98124–2207, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–300, 747–400, 747– 400D, and 747SR series airplanes. That NPRM was published in the Federal Register on September 16, 2005 (70 FR 54677). That NPRM proposed to require a one-time inspection to determine whether any steel doubler (small or large) is installed at the lower forward and upper aft corners of the fuselage cutout at main entry doors (MEDs) number 3. Depending on the results of this inspection, that AD also proposed to require repetitive inspections for cracks of the skin, bearstrap, and small steel doubler (if installed) at the applicable corner or corners of the fuselage cutouts, and related investigative/corrective actions if necessary. That AD also proposed the optional terminating action for the repetitive inspections of installing a large steel doubler at the affected corners. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Revise Paragraph (h) to Include Reference to Small Steel Doubler Boeing requests that we revise paragraph (h) ‘‘Inspection for Steel Doublers’’ of the NPRM to include instructions to inspect the small steel doubler (if installed) for cracks. Boeing points out that this inspection is E:\FR\FM\22MRR1.SGM 22MRR1

Agencies

[Federal Register Volume 71, Number 55 (Wednesday, March 22, 2006)]
[Rules and Regulations]
[Pages 14367-14370]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-2677]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22383; Directorate Identifier 2005-NM-102-AD; 
Amendment 39-14520; AD 2006-06-11]
RIN 2120-AA64


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

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Boeing Model 747-100B SUD, 747-300, 747-400, and 747-400D series 
airplanes; and Model 747-200B series airplanes having a stretched upper 
deck. This AD requires repetitively inspecting for cracking or 
discrepancies of the fasteners in the tension ties, shear webs, and 
frames at body stations 1120 through 1220, and performing related 
investigative and corrective actions if necessary. This AD results from 
new reports of severed tension ties, as well as numerous reports of 
cracked tension ties, broken fasteners, and cracks in the frame, shear 
web, and shear ties adjacent to tension ties for the upper deck. We are 
issuing this AD to detect and correct cracking of the tension ties, 
shear webs, and frames of the upper deck, which could result in rapid 
decompression of the airplane.

DATES: This AD becomes effective April 26, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of April 26, 
2006.

ADDRESSES: You may examine the AD docket on the Internet at http://
dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe 
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98055-4056; telephone (425) 917-6437; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing Model 
747-100B SUD, 747-300, 747-400, and 747-400D series airplanes; and 
Model 747-200B series airplanes having a stretched upper deck (SUD). 
That NPRM was published in the Federal Register on September 12, 2005 
(70 FR 53743). That NPRM proposed to require repetitively inspecting 
for cracking or discrepancies of the fasteners in the tension ties, 
shear webs, and frames at body stations 1120 through 1220, and related 
investigative and corrective actions if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request To Discuss Special Freighters

    The Boeing Company (hereafter referred to in this AD as ``Boeing'') 
requests that we revise the Discussion section of the proposed AD to 
refer to Boeing Model 747-200B(SUD)SF, 747-300SF, and 747-400SF 
airplanes. Boeing notes that the Discussion section mentions Boeing 
747-200B series airplanes modified under a Boeing-

[[Page 14368]]

owned supplemental type certificate (STC) to include a SUD, but doesn't 
mention STCs and service bulletins related to converting airplanes into 
a special freighter configuration. Boeing requests that we add a 
paragraph to the Discussion section stating that certain ``Boeing Model 
747-200B(SUD), 747-300, and 747-400 series airplanes'' have been 
modified to a special freighter configuration and are subject to the 
identified unsafe condition for the tension ties and frames at body 
stations (BS) 1120 through 1220 only. Boeing contends that tension ties 
and frames at BS 880 through 1100 on the airplanes configured as 
special freighters are more robust and are not subject to the unsafe 
condition. Boeing states that adding such a paragraph would clarify 
that special freighters are affected by the AD, but that tension ties 
and frames at BS 880 through 1100 are not subject to the AD.
    We agree that a special freighter that is converted from a Boeing 
747-200B series airplane having a SUD or from a Boeing 747-300 or -400 
series airplane is subject to the unsafe condition addressed by this 
AD. These airplanes are already included in the applicability of this 
AD. However, we do not agree with Boeing's request to refer to tension 
ties and frames at BS 880 through 1100 on the airplanes converted to 
special freighters because we have not indicated that the tension ties 
and frames in this area are subject to the AD. The Discussion section 
of the proposed AD is not restated in the final rule, so we have made 
no change with regard to Boeing's request.

Request To Clarify Effect on Other ADs

    Boeing also requests that we clarify paragraph (b) of the proposed 
AD to state that, for special freighters that are converted from a 
Boeing 747-200B series airplane having a SUD or from a Boeing 747-300 
or -400 series airplane, the inspections in this AD will not terminate 
the inspections of structural significant item (SSI) F-19A of Boeing 
Document No. D6-35022, ``Supplemental Structural Inspection Document 
(SSID),'' Revision G, dated December 2000 (hereafter referred to in 
this AD as ``the SSID'') for BS 880 through 1100.
    We agree that this AD does not terminate the inspections of SSI F-
19A for BS 880 through 1100. As we stated previously, tension ties and 
frames in BS 880 through 1100 are not subject to this AD. For 
clarification, we have revised paragraph (b) of this AD to state that 
the provisions of that paragraph apply only to areas inspected in 
accordance with this AD.

Request To Clarify Compliance Times

    Boeing also requests that we revise paragraph (f)(1) of the 
proposed AD to state that the provision in that paragraph applies only 
to airplanes identified in Boeing Alert Service Bulletin 747-53A2507. 
Boeing states that, without this clarification, operators may question 
whether paragraph (f)(1) applies to all airplanes versus all airplanes 
specified in Boeing Alert Service Bulletin 747-53A2507.
    We do not agree with Boeing's request to clarify the compliance 
times. Paragraph (f) of this AD refers to paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 747-53A2507 as the 
source for compliance times, ``except as provided by paragraphs (f)(1), 
(f)(2), and (f)(3) of this AD.'' The compliance times in that service 
bulletin are also summarized in the preamble of the NPRM. We explained 
in the preamble of the NPRM, under the heading ``Clarification of 
Compliance Time for Stage 1 Inspections,'' that this AD applies to 
certain airplanes not subject to the inspection in Boeing Service 
Bulletin 747-53-2483. Paragraph (f)(1) is intended to clarify the 
applicable compliance time for the Stage 1 inspections for these 
airplanes. We find that no further clarification of the compliance 
times is needed.

Request To Correct Typographical Error

    Boeing also requests that we revise paragraph (c) of the proposed 
AD to refer to Model 747-200B series airplanes instead of ``Model 747-
200 series airplanes.'' We agree. A typographical error resulted in the 
omission of the letter ``B'' from the model. We have revised paragraph 
(c) of this AD accordingly.

Clarification of Applicability

    The proposed AD specified that the actions therein would be 
applicable to ``Boeing Model 747-100B SUD, 747-300, 747-400, and 747-
400D series airplanes; and Model 747-200[B] series airplanes having a 
stretched upper deck; certificated in any category; as identified in 
Boeing Alert Service Bulletin 747-53A2507, dated April 21, 2005.'' The 
current effectivity listing in the service bulletin includes airplanes 
up to and including line number 1358. However, the service bulletin 
also specifies that airplanes after line number 1358 are affected. 
Therefore, for clarification, we have revised this AD to apply to all 
airplanes of the affected models.

Clarification of Alternative Method of Compliance (AMOC) Paragraph

    We have revised this action to clarify the appropriate procedure 
for notifying the principal inspector before using any approved AMOC on 
any airplane to which the AMOC applies.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Interim Action

    We consider this AD interim action. The manufacturer is currently 
developing a modification that will address the unsafe condition 
identified in this AD. Once this modification is developed, approved, 
and available, we may consider additional rulemaking.

Costs of Compliance

    There are about 622 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                  Number of
                                                 Average                            U.S.-
             Action                Work hours   labor rate   Cost per airplane    registered      Fleet cost
                                                 per hour                         airplanes
----------------------------------------------------------------------------------------------------------------
Stage 1 Inspection per                     19          $65  $1,235, per                   76  $93,860, per
 inspection cycle.\1\                                        inspection cycle.                 inspection
                                                                                               cycle.\1\

[[Page 14369]]

 
Stage 2 Inspection, per                    83           65  $5,395, per                   76  $410,020, per
 inspection cycle.                                           inspection cycle.                 inspection cycle.
----------------------------------------------------------------------------------------------------------------
1 Completing the initial Stage 2 inspection ends the repetitive Stage 1 inspections.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-06-11 Boeing: Amendment 39-14520. Docket No. FAA-2005-22383; 
Directorate Identifier 2005-NM-102-AD.

Effective Date

    (a) This AD becomes effective April 26, 2006.

Affected ADs

    (b) For the areas inspected in accordance with this AD, 
accomplishing the requirements of paragraph (f) of this AD 
terminates the corresponding inspection requirements for the upper 
deck tension ties as required by paragraphs (c) and (d) of AD 2004-
07-22, amendment 39-13566, as those paragraphs apply to inspections 
of structural significant item (SSI) F-19A, as identified in Boeing 
Document No. D6-35022, ``Supplemental Structural Inspection 
Document,'' Revision G, dated December 2000. All other requirements 
of AD 2004-07-22 continue to apply.

Applicability

    (c) This AD applies to all Boeing Model 747-100B SUD, 747-300, 
747-400, and 747-400D series airplanes; and Model 747-200B series 
airplanes having a stretched upper deck; certificated in any 
category.

Unsafe Condition

    (d) This AD results from new reports of severed tension ties, as 
well as numerous reports of cracked tension ties, broken fasteners, 
and cracks in the frame, shear web, and shear ties adjacent to 
tension ties for the upper deck. We are issuing this AD to detect 
and correct cracking of the tension ties, shear webs, and frames of 
the upper deck, which could result in rapid decompression of the 
airplane.

Compliance

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

Repetitive Inspections and Corrective Actions

    (f) Do repetitive detailed and high frequency eddy current 
inspections, as applicable, for cracking or discrepancies of the 
fasteners in the tension ties, shear webs, and frames at body 
stations 1120 through 1220, and related investigative and corrective 
actions as applicable, by doing all actions in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2507, dated April 21, 2005, except as provided by paragraphs (g) 
and (h) of this AD. Do the initial and repetitive Stage 1 and Stage 
2 inspections at the applicable times specified in Paragraph 1.E., 
``Compliance,'' of the service bulletin, except as provided by 
paragraphs (f)(1), (f)(2), and (f)(3) of this AD. Any applicable 
investigative and corrective actions must be done before further 
flight. Doing the initial Stage 2 inspection ends the repetitive 
Stage 1 inspections.
    (1) For any airplane not identified in and subject to 
inspections in accordance with Boeing Service Bulletin 747-53-2483: 
Do the initial Stage 1 inspection in accordance with Boeing Alert 
Service Bulletin 747-53A2507 before the accumulation of 8,000 total 
flight cycles, or within 1,500 flight cycles after the effective 
date of this AD, whichever is later.
    (2) Where Paragraph 1.E., ``Compliance,'' of the service 
bulletin specifies a compliance time relative to the original issue 
date of the service bulletin, this AD requires compliance before the 
specified compliance time after the effective date of this AD.
    (3) For any airplane that reaches the applicable compliance time 
for the initial Stage 2 inspection (as specified in Table 1, 
Compliance Recommendations, under paragraph 1.E. of the service 
bulletin) before reaching the applicable compliance time for the 
initial Stage 1 inspection: Doing the initial Stage 2 inspection 
eliminates the need to do the Stage 1 inspection.

Exception to Corrective Action Instructions

    (g) If any discrepancy; including but not limited to cracking, 
or broken, loose, or missing fasteners; is found during any 
inspection required by this AD, and Boeing Alert Service Bulletin 
747-53A2507, dated April 21, 2005, specifies to contact Boeing for 
appropriate action: Before further flight, repair the discrepancy 
using a method approved in accordance with the procedures specified 
in paragraph (i) of this AD.

[[Page 14370]]

No Reporting Requirement

    (h) Although Boeing Alert Service Bulletin 747-53A2507, dated 
April 21, 2005, specifies reporting inspection findings to the 
manufacturer, this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (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.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 747-53A2507, 
dated April 21, 2005, to perform the actions that are required by 
this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approved the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street, SW., room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/
code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 9, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-2677 Filed 3-21-06; 8:45 am]
BILLING CODE 4910-13-P