Airworthiness Directives; Boeing Model 777-200 Series Airplanes, 45348-45350 [E8-17749]

Download as PDF 45348 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations Actions and Compliance the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–16–06 BAE Systems (Operations) Limited (Formerly British Aerospace Regional Aircraft): Amendment 39– 15624. Docket No. FAA–2008–0541; Directorate Identifier 2008–NM–063–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 9, 2008. Affected ADs (b) None. Applicability (c) This AD applies to all BAE Systems (Operations) Limited Model Jetstream 4101 airplanes, certificated in any category, all serial numbers. Subject dwashington3 on PRODPC61 with RULES Reason (e) The mandatory continuing airworthiness information (MCAI) states: Resulting from the assessment of fuel tank wiring installations required by SFAR 88 (Special Federal Aviation Regulation 88) and equivalent JAA/EASA (Joint Aviation Authorities/European Aviation Safety Agency) policy, BAE Systems identified two features in the Jetstream 4100 where the need for design changes was apparent. One of these is addressed by Service Bulletin (SB) J41–28–013 which introduces additional bonding leads between pipes, structure and various components to improve the electrical bond paths within the fuel tank areas. This design change is identified by modification number JM41659. Additionally, SB J41–28– 013 provides instructions to inspect the existing bonding leads, to replace any defective leads and to examine all fuel system pipe runs in the wings to ensure appropriate clearances are maintained. Insufficient or defective bonding in the fuel tank area, if not corrected, could lead to ignition of fuel vapours and subsequent fuel tank explosion. For the reason stated above, this EASA Airworthiness Directive (AD) requires the installation of additional bonding leads, inspection [for defects] of existing bonding leads and [for clearance of] all fuel system pipe runs in the wings and follow-on corrective actions, as necessary. Corrective actions include replacing any defective bonding leads and adjusting clearances of the fuel system pipe runs. 12:53 Aug 04, 2008 Jkt 214001 FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. (d) Air Transport Association (ATA) of America Code 28: Fuel. VerDate Aug<31>2005 (f) Within 24 months after the effective date of this AD, unless already done, do the following actions. (1) Inspect the bonding leads between ribs 1 and 9, and between ribs 16 and 19, in the left-hand (LH) and right-hand (RH) wings in accordance with paragraph 2.B.(2) of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41–28–013, Revision 1, dated January 10, 2008; and, before next flight, replace all defective bonding leads with airworthy parts in accordance with the service bulletin. (2) Inspect all fuel system pipe runs inside the LH and RH wings in accordance with paragraph 2.B.(3) of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41–28–013, Revision 1, dated January 10, 2008; and, if incorrect clearances are found, before next flight, adjust clearances in accordance with the service bulletin. (3) Install additional electrical bonding of components within the LH and RH wings in accordance with paragraphs 2.B.(4) to 2.B.(15) of the Accomplishment Instructions of BAE Systems (Operations) Limited Service Bulletin J41–28–013, Revision 1, dated January 10, 2008. Other FAA AD Provisions Frm 00006 Fmt 4700 Sfmt 4700 Material Incorporated by Reference (i) You must use BAE Systems (Operations) Limited Service Bulletin J41–28–013, Revision 1, dated January 10, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact British Aerospace Regional Aircraft American Support, 13850 Mclearen Road, Herndon, Virginia 20171. (3) You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on July 23, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–17621 Filed 8–4–08; 8:45 am] BILLING CODE 4910–13–P (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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. PO 00000 Related Information (h) Refer to MCAI EASA Airworthiness Directive 2008–0040, dated February 27, 2008; and BAE Systems (Operations) Limited Service Bulletin J41–28–013, Revision 1, dated January 10, 2008; for related information. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0520; Directorate Identifier 2008–NM–018–AD; Amendment 39–15630; AD 2008–16–12] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777–200 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 777–200 series airplanes. This AD requires repetitive inspections for any wrinkle in certain external skin panels, and for cracking at the fuselage bulkhead shear tie end fastener locations at certain stations of Section 48 of the fuselage; and doing related investigative and corrective actions if necessary. This AD results from a report of cracks found in the external skin on the left and right sides of the Section 48 panel of the fuselage on two airplanes E:\FR\FM\05AUR1.SGM 05AUR1 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations 45349 with skin wrinkles found at two of the external crack locations. We are issuing this AD to detect and correct wrinkles and cracks in certain external skin panels of Section 48, which could join together and result in reduced structural integrity of support structure for the vertical and horizontal stabilizers and inability of the airplane to sustain limit loads. DATES: This AD is effective September 9, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 9, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. considered the comment received. Boeing concurs with the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed. 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. Examining the AD Docket 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. You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6452; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: dwashington3 on PRODPC61 with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 777–200 series airplanes. That NPRM was published in the Federal Register on May 7, 2008 (73 FR 25599). That NPRM proposed to require repetitive inspections for any wrinkle in certain external skin panels, and for cracking at the fuselage bulkhead shear tie end fastener locations at certain stations of Section 48 of the fuselage; and doing related investigative and corrective actions if necessary. Comments We gave the public the opportunity to participate in developing this AD. We VerDate Aug<31>2005 12:53 Aug 04, 2008 Jkt 214001 Costs of Compliance We estimate that the inspections in this AD affect 13 airplanes of U.S. registry. We also estimate that it takes about 15 work-hours per product to comply with this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $15,600, or $1,200 per product, per inspection cycle. Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), 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. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–16–12 Boeing: Amendment 39–15630. Docket No. FAA–2008–0520; Directorate Identifier 2008–NM–018–AD. Effective Date (a) This airworthiness directive (AD) is effective September 9, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 777–200 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 777–53A0051, dated November 8, 2007. Unsafe Condition (d) This AD results from a report of cracks found in the external skin on the left and right sides of the Section 48 fuselage panel on two airplanes with skin wrinkles found at two of the external crack locations. We are issuing this AD to detect and correct wrinkles and cracks in certain external skin panels of Section 48, which could join together and result in reduced structural integrity of support structure for the vertical and horizontal stabilizers and inability of the airplane to sustain limit loads. Compliance (e) Comply with this AD within the compliance times specified, unless already done. Repetitive Inspections/Investigative and Corrective Actions (f) At the applicable compliance times specified in paragraph 1.E., ‘‘Compliance’’ of Boeing Alert Service Bulletin 777–53A0051, dated November 8, 2007; except as provided by paragraph (g) of this AD: Do the applicable inspections for any wrinkle of the external skin and for cracking at the fuselage bulkhead shear tie end fastener locations at Stations 2195.75, 2221.65, and 2245.70 of the Section 48 panel of the fuselage, between E:\FR\FM\05AUR1.SGM 05AUR1 45350 Federal Register / Vol. 73, No. 151 / Tuesday, August 5, 2008 / Rules and Regulations stringers 5 and 10 on the left and right sides; and do all the applicable investigative and corrective actions; by doing all of the applicable actions in accordance with the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Do all applicable investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified in paragraph 1.E. of the service bulletin. Exception to Compliance Times (g) Where Boeing Alert Service Bulletin 777–53A0051, dated November 8, 2007, specifies counting the compliance time from ‘‘* * * the date on this service bulletin,’’ this AD requires counting the compliance time from the effective date of this AD. Exception to Corrective Actions (h) If any damage beyond the repair limits specified in Boeing Alert Service Bulletin 777–53A0051, dated November 8, 2007, is found during any inspection required by this AD, and the service bulletin 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 (i) of this AD. dwashington3 on PRODPC61 with RULES Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Duong Tran, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6452; fax (425) 917–6590 has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (3) 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. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 777–53A0051, dated November 8, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. (3) You may review copies of the service information incorporated by reference at the VerDate Aug<31>2005 12:53 Aug 04, 2008 Jkt 214001 FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 23, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–17749 Filed 8–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0413; Directorate Identifier 2008–NM–003–AD; Amendment 39–15631; AD 2008–16–13] RIN 2120–AA64 Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. This AD requires replacing the pushrods for the left and right elevator tab control mechanisms with new, improved pushrods. This AD results from a report of a rod end fracture on a rudder power control unit (PCU) control rod, which is similar to the ones used for the elevator tab pushrods. Analysis revealed that the fractured rod end had an incorrect hardness, which had probably occurred during the manufacture of the control rod. We are issuing this AD to prevent fracture of the elevator tab pushrod ends, which could result in excessive in-flight vibrations of the elevator tab, possible loss of the elevator tab, and consequent loss of controllability of the airplane. DATES: This AD is effective September 9, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 9, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Frm 00008 Fmt 4700 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6421; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion Airworthiness Directives; Boeing Model 737–600, –700, –700C, –800, –900, and –900ER Series Airplanes PO 00000 Examining the AD Docket Sfmt 4700 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 737–600, –700, –700C, –800, –900, and –900ER series airplanes. That NPRM was published in the Federal Register on April 24, 2008 (73 FR 22090). That NPRM proposed to require replacing the pushrods for the left and right elevator tab control mechanisms with new, improved pushrods. Comments We gave the public the opportunity to participate in developing this AD. We considered the two comments received. Boeing concurs with the contents of the NPRM, and Continental Airlines has no issues with the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD affects 715 airplanes of U.S. registry. We also estimate that it takes about 4 work-hours per product to comply with this AD. The average labor rate is $80 per workhour. Required parts cost about $8,036 per product. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $5,974,540, or $8,356 per product. E:\FR\FM\05AUR1.SGM 05AUR1

Agencies

[Federal Register Volume 73, Number 151 (Tuesday, August 5, 2008)]
[Rules and Regulations]
[Pages 45348-45350]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-17749]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0520; Directorate Identifier 2008-NM-018-AD; 
Amendment 39-15630; AD 2008-16-12]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Boeing Model 777-200 series airplanes. This AD requires repetitive 
inspections for any wrinkle in certain external skin panels, and for 
cracking at the fuselage bulkhead shear tie end fastener locations at 
certain stations of Section 48 of the fuselage; and doing related 
investigative and corrective actions if necessary. This AD results from 
a report of cracks found in the external skin on the left and right 
sides of the Section 48 panel of the fuselage on two airplanes

[[Page 45349]]

with skin wrinkles found at two of the external crack locations. We are 
issuing this AD to detect and correct wrinkles and cracks in certain 
external skin panels of Section 48, which could join together and 
result in reduced structural integrity of support structure for the 
vertical and horizontal stabilizers and inability of the airplane to 
sustain limit loads.

DATES: This AD is effective September 9, 2008.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 9, 
2008.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Duong Tran, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6452; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
certain Boeing Model 777-200 series airplanes. That NPRM was published 
in the Federal Register on May 7, 2008 (73 FR 25599). That NPRM 
proposed to require repetitive inspections for any wrinkle in certain 
external skin panels, and for cracking at the fuselage bulkhead shear 
tie end fastener locations at certain stations of Section 48 of the 
fuselage; and doing related investigative and corrective actions if 
necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Boeing concurs with the 
NPRM.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed.

Costs of Compliance

    We estimate that the inspections in this AD affect 13 airplanes of 
U.S. registry. We also estimate that it takes about 15 work-hours per 
product to comply with this AD. The average labor rate is $80 per work-
hour. Based on these figures, we estimate the cost of this AD to the 
U.S. operators to be $15,600, or $1,200 per product, per 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

    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.
    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.

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

2008-16-12 Boeing: Amendment 39-15630. Docket No. FAA-2008-0520; 
Directorate Identifier 2008-NM-018-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective September 9, 
2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 777-200 series airplanes, 
certificated in any category; as identified in Boeing Alert Service 
Bulletin 777-53A0051, dated November 8, 2007.

Unsafe Condition

    (d) This AD results from a report of cracks found in the 
external skin on the left and right sides of the Section 48 fuselage 
panel on two airplanes with skin wrinkles found at two of the 
external crack locations. We are issuing this AD to detect and 
correct wrinkles and cracks in certain external skin panels of 
Section 48, which could join together and result in reduced 
structural integrity of support structure for the vertical and 
horizontal stabilizers and inability of the airplane to sustain 
limit loads.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Repetitive Inspections/Investigative and Corrective Actions

    (f) At the applicable compliance times specified in paragraph 
1.E., ``Compliance'' of Boeing Alert Service Bulletin 777-53A0051, 
dated November 8, 2007; except as provided by paragraph (g) of this 
AD: Do the applicable inspections for any wrinkle of the external 
skin and for cracking at the fuselage bulkhead shear tie end 
fastener locations at Stations 2195.75, 2221.65, and 2245.70 of the 
Section 48 panel of the fuselage, between

[[Page 45350]]

stringers 5 and 10 on the left and right sides; and do all the 
applicable investigative and corrective actions; by doing all of the 
applicable actions in accordance with the Accomplishment 
Instructions of the service bulletin, except as provided by 
paragraph (h) of this AD. Do all applicable investigative and 
corrective actions before further flight. Repeat the applicable 
inspections thereafter at the applicable intervals specified in 
paragraph 1.E. of the service bulletin.

Exception to Compliance Times

    (g) Where Boeing Alert Service Bulletin 777-53A0051, dated 
November 8, 2007, specifies counting the compliance time from ``* * 
* the date on this service bulletin,'' this AD requires counting the 
compliance time from the effective date of this AD.

Exception to Corrective Actions

    (h) If any damage beyond the repair limits specified in Boeing 
Alert Service Bulletin 777-53A0051, dated November 8, 2007, is found 
during any inspection required by this AD, and the service bulletin 
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 (i) of this AD.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
FAA, ATTN: Duong Tran, Aerospace Engineer, Airframe Branch, ANM-
120S, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; 
telephone (425) 917-6452; fax (425) 917-6590 has the authority to 
approve AMOCs for this AD, if requested using the procedures found 
in 14 CFR 39.19.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.
    (3) 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.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 777-53A0051, 
dated November 8, 2007, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    (3) You may review copies of the service information 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on July 23, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-17749 Filed 8-4-08; 8:45 am]
BILLING CODE 4910-13-P
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