Airworthiness Directives; Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes, 59266-59268 [05-20075]

Download as PDF 59266 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations TABLE 1.—AFFECTED ELEVATOR PART NUMBERS AND SERIAL NUMBERS—Continued Part Right-hand elevator assembly Affected part numbers F55280000001, F55280000005 Inspections (h) If the left- or right-hand elevator assembly has a part number and serial number combination identified in Table 1 of this AD: Before further flight after accomplishing paragraph (g) of this AD, do the actions in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable. (1) Perform an endoscopic inspection to detect damage (such as a scratch, disbonding, or a tear), and a tap test and a thermographic inspection to detect signs of moisture penetration, to the upper and lower elevator panels on both sides of the airplane, in accordance with the service bulletin. (2) If any damage is found, before further flight, do all applicable corrective actions (including but not limited to repeating the thermographic inspection to determine the size of the damaged area, and performing a tap test around the areas where moisture is indicated), in accordance with the service bulletin. (3) Re-protect the elevator assembly (including performing a general visual inspection to determine if the drainage holes are clean, a general visual inspection to determine the condition of the sealant covering the static discharges contour, and applicable corrective actions), in accordance with the service bulletin. Note 1: For the purposes of this AD, a general visual inspection is: ‘‘A visual examination of an interior or exterior area, installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ Parts Installation (i) As of the effective date of this AD, no person may install, on any airplane, an elevator assembly having a part number and serial number combination identified in Table 1 of this AD unless the actions required by paragraph (h) of this AD are accomplished. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, International Branch, ANM–116, 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 VerDate Aug<31>2005 16:47 Oct 11, 2005 Affected serial numbers Jkt 208001 CG1002 through CG1094 inclusive, CG2001. airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Related Information (k) French airworthiness directive F–2004– 118 R1, dated October 13, 2004, also addresses the subject of this AD. Material Incorporated by Reference (l) You must use Airbus Service Bulletin A330–55–3032, excluding Appendix 01, dated December 22, 2003; or Airbus Service Bulletin A340–55–4029, excluding Appendix 01, dated December 22, 2003; as applicable; 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 these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, 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/federalregister/cfr/ibr-locations.html. Issued in Renton, Washington, on September 29, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–20064 Filed 10–11–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2003–NM–238–AD; Amendment 39–14330; AD 2005–20–33] RIN 2120–AA64 Airworthiness Directives; Boeing Model 727, 727C, 727–100, and 727– 100C Series Airplanes Federal Aviation Administration, DOT. ACTION: Final rule. AGENCY: SUMMARY: This amendment adopts a new airworthiness directive (AD), PO 00000 Frm 00058 Fmt 4700 Sfmt 4700 applicable to certain Boeing Model 727, 727C, 727–100, and 727–100C series airplanes. This AD requires repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, and corrective action if necessary. The actions specified by this AD are intended to detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe FCD cutout, which could result in the loss of the FCD and rapid decompression of the airplane. This action is intended to address the identified unsafe condition. Effective November 16, 2005. The incorporation by reference of a certain publication listed in the regulations is approved by the Director of the Federal Register as of November 16, 2005. DATES: The service information referenced in this AD may be obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6456; fax (425) 917–6590. A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Boeing Model 727, 727C, 727–100, and 727– 100C series airplanes was published as a supplemental notice of proposed rulemaking (NPRM) in the Federal Register on August 22, 2005 (70 FR 48904). That action proposed to require repetitive inspections of the frame inner chord, outer chord, and web of the forward and aft edge frames of the lower lobe forward cargo door cutout, and corrective action if necessary. SUPPLEMENTARY INFORMATION: E:\FR\FM\12OCR1.SGM 12OCR1 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations 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. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. The commenter supports the supplemental NPRM. 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 final rule to be an 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. Cost Impact There are approximately 211 airplanes of the affected design in the worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry will be affected by this AD, that it will take approximately 6 to 8 work hours per airplane to accomplish the required inspections, and that the average labor rate is $65 per work hour. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be between $45,240 and $60,320, or between $390 and $520 per airplane. The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions. VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 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 Impact The regulations adopted herein 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. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132. For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PO 00000 Frm 00059 Fmt 4700 Sfmt 4700 59267 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: I 2005–20–33 Boeing: Amendment 39–14330. Docket 2003–NM–238–AD. Applicability: Model 727, 727C, 727–100, and 727–100C series airplanes, line numbers 1 through 694 inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To detect and correct fatigue cracking of the forward and aft edge frames of the lower lobe forward cargo door (FCD) cutout, which could result in the loss of the FCD and rapid decompression of the airplane, accomplish the following: Note 1: This AD is related to AD 98–11– 03 R1, amendment 39–10983, and affects Structural Significant Item (SSI) F–11B of the Boeing 727 Supplemental Structural Inspection Document (SSID) program, D6– 48040–1, Revision H, dated June 1994. Initial and Repetitive Inspections (a) For airplanes on which the forward and aft edge frames of the lower lobe FCD cutout have not been inspected per AD 98–11–03 R1 as of the effective date of this AD: Prior to the accumulation of 21,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do the inspections specified in paragraph (c) of this AD. (b) For airplanes on which the forward and aft edge frames of the lower lobe FCD cutout have been inspected per AD 98–11–03 R1 as of the effective date of this AD: Within the next scheduled inspection required by AD 98–11–03 R1, or within 3,000 flight cycles after the effective date of this AD, whichever occurs first, do the inspections specified in paragraph (c) of this AD. (c) At the time specified in paragraph (a) or paragraph (b) of this AD, as applicable: Perform the detailed and high frequency eddy current inspections for cracks in the web and the inner and outer chords of the forward and aft frames of the forward cargo doorway in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 727–53A0229, dated March 24, 2005. Repeat the inspections thereafter at intervals not to exceed 3,000 flight cycles. Corrective Action (d) If any crack is found during any inspection required by paragraph (c) of this AD: Before further flight, repair per a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the E:\FR\FM\12OCR1.SGM 12OCR1 59268 Federal Register / Vol. 70, No. 196 / Wednesday, October 12, 2005 / Rules and Regulations Manager, Seattle ACO, to make those findings. For a repair method to be approved, the approval must meet the certification basis of the airplane, and the approval must specifically reference this AD. Certain Actions Constitute Compliance With AD 98–11–03 R1 (e) Accomplishment of the inspections specified in paragraph (c) of this AD is terminating action for the inspections required by AD 98–11–03 R1 that pertain to SSI F–11B of Boeing Document D6–48040–1, Boeing 727 SSID, Revision H, dated June 1994, for the areas specified in paragraph (c) of this AD only. Accomplishment of the actions required by paragraph (c) of this AD does not terminate the inspections required by AD 98–11–03 R1 for the remaining areas of SSI F–11B and does not terminate the remaining requirements of AD 98–11–03 R1. No Reporting Required (f) Although the service bulletin referenced in this AD specifies to provide certain information to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, is authorized to approve alternative methods of compliance (AMOCs) for this AD. (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. Incorporation by Reference (h) Unless otherwise specified in this AD, the actions must be done in accordance with Boeing Alert Service Bulletin 727–53A0229, dated March 24, 2005. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to 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. Effective Date (i) This amendment becomes effective on November 16, 2005. Issued in Renton, Washington, on September 29, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–20075 Filed 10–11–05; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 16:47 Oct 11, 2005 Jkt 208001 40 CFR Part 180 DC 20460–0001; telephone number:(703) 308–9367; e-mail address: Sec-18-Mailbox@epa.gov. SUPPLEMENTARY INFORMATION: [OPP–2005–0260; FRL–7738–8] I. General Information Imidacloprid; Pesticide Tolerances for Emergency Exemptions A. Does this Action Apply to Me? ENVIRONMENTAL PROTECTION AGENCY Environmental Protection Agency (EPA). ACTION: Final rule. AGENCY: SUMMARY: This regulation establishes a time-limited tolerance for the combined residues of imidacloprid, (1-[6-chloro-3pyridinyl) methyl]-N-nitro-2imidazolidinimine) and its metabolites containing the 6-chloropyridinyl moiety, all expressed as parent in or on pomegranates. This action is in response to EPA’s granting of an emergency exemption under section 18 of the Federal Insecticide, Fungicide, and Rodenticide Act (FIFRA) authorizing use of the pesticide on pomegranates. This regulation establishes a maximum permissible level for residues of imidacloprid in this food commodity. The tolerance will expire and is revoked on December 31, 2008. DATES: This regulation is effective October 12, 2005. Objections and requests for hearings must be received on or before December 12, 2005. ADDRESSES: To submit a written objection or hearing request follow the detailed instructions as provided in Unit VII. of the SUPPLEMENTARY INFORMATION. EPA has established a docket for this action under docket identification (ID) number OPP–2005– 0260. All documents in the docket are listed in the EDOCKET index at http:// www.epa.gov/edocket. Although listed in the index, some information is not publicly available, i.e., CBI or other information whose disclosure is restricted by statute. Certain other material, such as copyrighted material, is not placed on the Internet and will be publicly available only in hard copy form. Publicly available docket materials are available either electronically in EDOCKET or in hard copy at the Public Information and Records Integrity Branch (PIRIB), Rm. 119, Crystal Mall #2, 1801 S. Bell St., Arlington, VA. This docket facility is open from 8:30 a.m. to 4 p.m., Monday through Friday, excluding legal holidays. The docket telephone number is (703) 305–5805. FOR FURTHER INFORMATION CONTACT: Andrew Ertman, Registration Division (7505C), Office of Pesticide Programs, Environmental Protection Agency, 1200 Pennsylvania Ave., NW., Washington, PO 00000 Frm 00060 Fmt 4700 Sfmt 4700 You may be potentially affected by this action if you are an agricultural producer, food manufacturer, or pesticide manufacturer. Potentially affected entities may include, but are not limited to: • Crop production (NAICS code 111) • Animal production (NAICS code 112) • Food manufacturing (NAICS code 311) • Pesticide manufacturing (NAICS code 32532) This listing is not intended to be exhaustive, but rather provides a guide for readers regarding entities likely to be affected by this action. Other types of entities not listed in this unit could also be affected. The North American Industrial Classification System (NAICS) codes have been provided to assist you and others in determining whether this action might apply to certain entities. If you have any questions regarding the applicability of this action to a particular entity, consult the person listed under FOR FURTHER INFORMATION CONTACT. B. How Can I Access Electronic Copies of this Document and Other Related Information? In addition to using EDOCKET (http:// www.epa.gov/edocket/), you may access this Federal Register document electronically through the EPA Internet under the ‘‘Federal Register’’ listings at http://www.epa.gov/fedrgstr/. A frequently updated electronic version of 40 CFR part 180 is available on E-CFR Beta Site Two at http:// www.gpoaccess.gov/ecfr/. II. Background and Statutory Findings EPA, on its own initiative, in accordance with sections 408(e) and 408 (l)(6) of the Federal Food, Drug, and Cosmetic Act (FFDCA), 21 U.S.C. 346a, is establishing a tolerance for the combined residues of imidacloprid, (1[6-chloro-3-pyridinyl) methyl]-N-nitro2-imidazolidinimine) and its metabolites containing the 6chloropyridinyl moiety, all expressed as parent in or on pomegranates at 0.20 parts per million (ppm). This tolerance will expire and is revoked on December 31, 2008. EPA will publish a document in the Federal Register to remove the revoked tolerance from the Code of Federal Regulations. E:\FR\FM\12OCR1.SGM 12OCR1

Agencies

[Federal Register Volume 70, Number 196 (Wednesday, October 12, 2005)]
[Rules and Regulations]
[Pages 59266-59268]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-20075]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-238-AD; Amendment 39-14330; AD 2005-20-33]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, and 
727-100C Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Boeing Model 727, 727C, 727-100, and 727-100C 
series airplanes. This AD requires repetitive inspections of the frame 
inner chord, outer chord, and web of the forward and aft edge frames of 
the lower lobe forward cargo door (FCD) cutout, and corrective action 
if necessary. The actions specified by this AD are intended to detect 
and correct fatigue cracking of the forward and aft edge frames of the 
lower lobe FCD cutout, which could result in the loss of the FCD and 
rapid decompression of the airplane. This action is intended to address 
the identified unsafe condition.

DATES: Effective November 16, 2005.
    The incorporation by reference of a certain publication listed in 
the regulations is approved by the Director of the Federal Register as 
of November 16, 2005.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Boeing Model 727, 727C, 
727-100, and 727-100C series airplanes was published as a supplemental 
notice of proposed rulemaking (NPRM) in the Federal Register on August 
22, 2005 (70 FR 48904). That action proposed to require repetitive 
inspections of the frame inner chord, outer chord, and web of the 
forward and aft edge frames of the lower lobe forward cargo door 
cutout, and corrective action if necessary.

[[Page 59267]]

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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter supports the supplemental NPRM.

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 final rule to be an 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.

Cost Impact

    There are approximately 211 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 116 airplanes of U.S. registry 
will be affected by this AD, that it will take approximately 6 to 8 
work hours per airplane to accomplish the required inspections, and 
that the average labor rate is $65 per work hour. Based on these 
figures, the cost impact of the AD on U.S. operators is estimated to be 
between $45,240 and $60,320, or between $390 and $520 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

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 Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

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. Section 39.13 is amended by adding the following new airworthiness 
directive:

2005-20-33 Boeing: Amendment 39-14330. Docket 2003-NM-238-AD.

    Applicability: Model 727, 727C, 727-100, and 727-100C series 
airplanes, line numbers 1 through 694 inclusive; certificated in any 
category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To detect and correct fatigue cracking of the forward and aft 
edge frames of the lower lobe forward cargo door (FCD) cutout, which 
could result in the loss of the FCD and rapid decompression of the 
airplane, accomplish the following:

    Note 1: This AD is related to AD 98-11-03 R1, amendment 39-
10983, and affects Structural Significant Item (SSI) F-11B of the 
Boeing 727 Supplemental Structural Inspection Document (SSID) 
program, D6-48040-1, Revision H, dated June 1994.

Initial and Repetitive Inspections

    (a) For airplanes on which the forward and aft edge frames of 
the lower lobe FCD cutout have not been inspected per AD 98-11-03 R1 
as of the effective date of this AD: Prior to the accumulation of 
21,000 total flight cycles, or within 3,000 flight cycles after the 
effective date of this AD, whichever occurs later, do the 
inspections specified in paragraph (c) of this AD.
    (b) For airplanes on which the forward and aft edge frames of 
the lower lobe FCD cutout have been inspected per AD 98-11-03 R1 as 
of the effective date of this AD: Within the next scheduled 
inspection required by AD 98-11-03 R1, or within 3,000 flight cycles 
after the effective date of this AD, whichever occurs first, do the 
inspections specified in paragraph (c) of this AD.
    (c) At the time specified in paragraph (a) or paragraph (b) of 
this AD, as applicable: Perform the detailed and high frequency eddy 
current inspections for cracks in the web and the inner and outer 
chords of the forward and aft frames of the forward cargo doorway in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-53A0229, dated March 24, 2005. Repeat the 
inspections thereafter at intervals not to exceed 3,000 flight 
cycles.

Corrective Action

    (d) If any crack is found during any inspection required by 
paragraph (c) of this AD: Before further flight, repair per a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or according to data meeting the certification basis of 
the airplane approved by an Authorized Representative for the Boeing 
Commercial Airplanes Delegation Option Authorization Organization 
who has been authorized by the

[[Page 59268]]

Manager, Seattle ACO, to make those findings. For a repair method to 
be approved, the approval must meet the certification basis of the 
airplane, and the approval must specifically reference this AD.

Certain Actions Constitute Compliance With AD 98-11-03 R1

    (e) Accomplishment of the inspections specified in paragraph (c) 
of this AD is terminating action for the inspections required by AD 
98-11-03 R1 that pertain to SSI F-11B of Boeing Document D6-48040-1, 
Boeing 727 SSID, Revision H, dated June 1994, for the areas 
specified in paragraph (c) of this AD only. Accomplishment of the 
actions required by paragraph (c) of this AD does not terminate the 
inspections required by AD 98-11-03 R1 for the remaining areas of 
SSI F-11B and does not terminate the remaining requirements of AD 
98-11-03 R1.

No Reporting Required

    (f) Although the service bulletin referenced in this AD 
specifies to provide certain information to the manufacturer, this 
AD does not include that requirement.

Alternative Methods of Compliance

    (g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle 
ACO, is authorized to approve alternative methods of compliance 
(AMOCs) for this AD.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Incorporation by Reference

    (h) Unless otherwise specified in this AD, the actions must be 
done in accordance with Boeing Alert Service Bulletin 727-53A0229, 
dated March 24, 2005. This incorporation by reference was approved 
by the Director of the Federal Register in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. To get copies of this service information, 
contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207. To inspect copies of this service 
information, go to the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; or to 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.

Effective Date

    (i) This amendment becomes effective on November 16, 2005.

    Issued in Renton, Washington, on September 29, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-20075 Filed 10-11-05; 8:45 am]
BILLING CODE 4910-13-P