Airworthiness Directives; Boeing Model 777-200 and -300 Series Airplanes, 7681-7683 [05-2838]

Download as PDF Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules measurement of the flame arrestor’s position in the pump, and any applicable corrective actions, by accomplishing all of the actions in the applicable alert service bulletin. Repeat the measurement of the flame arrestor’s position in the pump thereafter at intervals not to exceed 6,000 flight hours or 24 months, whichever is first. Any applicable corrective actions must be done before further flight. Note 2: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Note 3: There is no terminating action available at this time for the repetitive inspections required by paragraph (g) of this AD. Parts Installation (h) As of the effective date of this AD, no main tank fuel boost pump may be installed on any airplane unless it has been inspected, and any applicable corrective action performed, in accordance with the requirements of this AD. Alternative Methods of Compliance (AMOCs) (i) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on February 6, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–2839 Filed 2–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20350; Directorate Identifier 2004–NM–202–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 777–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 777–200 and –300 VerDate jul<14>2003 14:39 Feb 14, 2005 Jkt 205001 series airplanes. This proposed AD would require inspecting the valve control and indication wire bundles of the fuel system of the wing rear spar for discrepancies, and corrective action if necessary. This proposed AD is prompted by reports of six incidents of the wire bundles chafing against the rear spar stiffeners outside the fuel tank. We are proposing this AD to prevent this chafing, which could result in wire damage leading to a short circuit, subsequent ignition of flammable vapors, and possible uncontrollable fire during fueling or flight. DATES: We must receive comments on this proposed AD by April 1, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, room PL–401, Washington, DC 20590. • By fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. This docket number is FAA–2005– 20350; the directorate identifier for this docket is 2004–NM–202–AD. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Systems and Equipment Branch, ANM–130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6482; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Docket Management System (DMS) The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track each action and assign a corresponding PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 7681 directorate identifier. The DMS AD docket number is in the form ‘‘Docket No. FAA–2004–99999.’’ The Transport Airplane Directorate identifier is in the form ‘‘Directorate Identifier 2004–NM– 999–AD.’’ Each DMS AD docket also lists the directorate identifier (‘‘Old Docket Number’’) as a cross-reference for searching purposes. Comments Invited We invite you to submit any relevant written data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20350; Directorate Identifier 2004–NM–202–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments submitted by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of that website, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at https://www.faa.gov/language and https:// www.plainlanguage.gov. Examining the Docket You can examine the AD docket on the Internet at https://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 DOT street address stated in the ADDRESSES section. Comments will be available in E:\FR\FM\15FEP1.SGM 15FEP1 7682 Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules the AD docket shortly after the DMS receives them. We have included this information in paragraph (f) of this proposed AD. Discussion We have received reports indicating six incidents of the valve control and indication wire bundles of the fuel system chafing against the rear spar stiffeners outside the fuel tank on Boeing Model 777 series airplanes. Since this wire bundle is located in a high-vibration area, chafing can lead to potential wire damage, and a short circuit could occur. These conditions, if not corrected, could result in wire damage leading to a short circuit, subsequent ignition of flammable vapors, and possible uncontrollable fire during fueling or flight. Clarification of Inspection Terminology In this proposed AD, the ‘‘inspection’’ of the wire bundles, as specified in the service bulletin is referred to as a ‘‘detailed inspection.’’ We have included the definition for a detailed inspection in a note in the proposed AD. Relevant Service Information We have reviewed Boeing Special Attention Service Bulletin 777–28– 0033, dated August 14, 2003. The service bulletin describes procedures for inspecting the valve control and indication wire bundles of the fuel system of the wing rear spar for discrepancies (chafing damage and incorrect routing), and corrective action if necessary. The corrective action involves repairing any damage and modifying the wire bundle routing, as applicable. Accomplishing the actions specified in the service information is intended to adequately address the unsafe condition. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other airplanes of this same type design. Therefore, we are proposing this AD, which would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Difference Between the Proposed AD and Service Bulletin.’’ Difference Between the Proposed AD and Service Bulletin The proposed AD identifies the correct part number (P/N) for a certain clamp for which an incorrect P/N was specified in the service bulletin. P/N BACC10GU105P, shown in the part list table of Kit 005W3225 and in the step tables in Figures 3 and 4 of the Accomplishment Instructions of the service bulletin, is not a valid P/N; the correct P/N is BACC10JU105P. The manufacturer is aware of this discrepancy, concurs with the change, and has issued Information Notice (IN) 777–28–0033 IN 01, dated January 29, 2004, to inform operators of the error. VerDate jul<14>2003 14:39 Feb 14, 2005 Jkt 205001 Costs of Compliance There are about 403 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 129 airplanes of U.S. registry. The proposed inspection would take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the proposed inspection for U.S. operators is $8,385, or $65 per airplane. Authority for This Rulemaking The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated 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 proposed AD. Regulatory Findings We have determined that this proposed AD will not have federalism implications under Executive Order 13132. This proposed 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 the proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. 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, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2005–20350; Directorate Identifier 2004–NM–202–– AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this AD action by April 1, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 777– 200 and –300 series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 777–28–0033, dated August 14, 2003. Unsafe Condition (d) This AD was prompted by reports of six incidents of the valve control and indication wire bundles of the fuel system chafing against the rear spar stiffeners outside the fuel tank. We are issuing this AD to prevent this chafing, which could result in wire damage leading to a short circuit, subsequent ignition of flammable vapors, and possible uncontrollable fire during fueling or flight. 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. Detailed Inspection/Corrective Action (f) Within 18 months after the effective date of this AD: Do a detailed inspection of the valve control and indication wire bundles of the fuel system of the wing rear spar for discrepancies (including any applicable corrective action), by doing all the actions specified in the Accomplishment Instructions of Boeing Special Attention E:\FR\FM\15FEP1.SGM 15FEP1 Federal Register / Vol. 70, No. 30 / Tuesday, February 15, 2005 / Proposed Rules Service Bulletin 777–28–0033, dated August 14, 2003. Any applicable corrective action must be done before further flight. Part number (P/N) BACC10GU105P, shown in the part list table of Kit 005W3225 and in the step tables in Figures 3 and 4 of the Accomplishment Instructions of the service bulletin, is not a valid P/N; the correct P/N that must be used is P/N BACC10JU105P. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ Alternative Methods of Compliance (AMOCs) (g) The Manager, Seattle Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Issued in Renton, Washington, on February 6, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–2838 Filed 2–14–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20349; Directorate Identifier 2003–NM–108–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model MD–11 and –11F Airplanes; Model DC–10–10 and DC– 10–10F Airplanes; Model DC–10–15 Airplanes; Model DC–10–30 and DC– 10–30F (KC–10A and KDC–10) Airplanes; Model DC–10–40 and DC– 10–40F Airplanes; and Model MD–10– 10F and MD–10–30F Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain McDonnell Douglas Model MD–11 and –11F airplanes. The existing AD currently requires a one-time inspection to detect loose preload-indicating (PLI) washers or cracked or corroded nuts of the lower bolts of the inboard flap VerDate jul<14>2003 16:12 Feb 14, 2005 Jkt 205001 outboard hinge, and replacement with new parts if necessary. This proposed AD would require replacement with new, improved parts of the inboard flap, outboard hinge, forward attach bracket, and lower attach bolt assemblies. This proposed AD also would add certain other McDonnell Douglas transport category airplanes and require an inspection for certain parts, and related investigative and corrective actions if necessary. This proposed AD is prompted by a report indicating that the left-hand inboard flap outboard hinge pulled away from the wing structure. We are proposing this AD to prevent loose PLI washers or cracked or corroded nuts of the lower bolts of the inboard flap outboard hinge, which could result in separation of the inboard flap outboard hinge from the wing structure and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by April 1, 2005. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, room PL–401, Washington, DC 20590. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024). You can examine the contents of this AD docket on the Internet at https:// dms.dot.gov, or at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, on the plaza level of the Nassif Building, Washington, DC. FOR FURTHER INFORMATION CONTACT: Ronald Atmur, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5224; fax (562) 627–5210. PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 7683 SUPPLEMENTARY INFORMATION: Docket Management System (DMS) The FAA has implemented new procedures for maintaining AD dockets electronically. As of May 17, 2004, new AD actions are posted on DMS and assigned a docket number. We track each action and assign a corresponding directorate identifier. The DMS AD docket number is in the form ‘‘Docket No. FAA–2005–99999.’’ The Transport Airplane Directorate identifier is in the form ‘‘Directorate Identifier 2005–NM– 999–AD.’’ Each DMS AD docket also lists the directorate identifier (‘‘Old Docket Number’’) as a cross-reference for searching purposes. Comments Invited We invite you to submit any written relevant data, views, or arguments regarding this proposed AD. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2005–20349; Directorate Identifier 2003–NM–108–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of our docket web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You can review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78), or you can visit https:// dms.dot.gov. We are reviewing the writing style we currently use in regulatory documents. We are interested in your comments on whether the style of this document is clear, and your suggestions to improve the clarity of our communications that affect you. You can get more information about plain language at https://www.faa.gov/language and https:// www.plainlanguage.gov. Examining the Docket You can examine the AD docket on the Internet at https://dms.dot.gov, or in person at the Docket Management E:\FR\FM\15FEP1.SGM 15FEP1

Agencies

[Federal Register Volume 70, Number 30 (Tuesday, February 15, 2005)]
[Proposed Rules]
[Pages 7681-7683]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2838]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20350; Directorate Identifier 2004-NM-202-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 777-200 and -300 Series 
Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for certain Boeing Model 777-200 and -300 series airplanes. This 
proposed AD would require inspecting the valve control and indication 
wire bundles of the fuel system of the wing rear spar for 
discrepancies, and corrective action if necessary. This proposed AD is 
prompted by reports of six incidents of the wire bundles chafing 
against the rear spar stiffeners outside the fuel tank. We are 
proposing this AD to prevent this chafing, which could result in wire 
damage leading to a short circuit, subsequent ignition of flammable 
vapors, and possible uncontrollable fire during fueling or flight.

DATES: We must receive comments on this proposed AD by April 1, 2005.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     By fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
    You can examine the contents of this AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2005-20350; the directorate identifier for this docket is 
2004-NM-202-AD.

FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Systems and 
Equipment Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6482; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS)

    The FAA has implemented new procedures for maintaining AD dockets 
electronically. As of May 17, 2004, new AD actions are posted on DMS 
and assigned a docket number. We track each action and assign a 
corresponding directorate identifier. The DMS AD docket number is in 
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane 
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier 
(``Old Docket Number'') as a cross-reference for searching purposes.

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2005-20350; 
Directorate Identifier 2004-NM-202-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments submitted by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that website, anyone can find and read the comments in any of our 
dockets, including the name of the individual who sent the comment (or 
signed the comment on behalf of an association, business, labor union, 
etc.). You can review DOT's complete Privacy Act Statement in the 
Federal Register published on April 11, 2000 (65 FR 19477-78), or you 
can visit https://dms.dot.gov.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications that affect you. You can get more information about 
plain language at https://www.faa.gov/language and https://
www.plainlanguage.gov.

Examining the Docket

    You can examine the AD docket on the Internet at https://
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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in

[[Page 7682]]

the AD docket shortly after the DMS receives them.

Discussion

    We have received reports indicating six incidents of the valve 
control and indication wire bundles of the fuel system chafing against 
the rear spar stiffeners outside the fuel tank on Boeing Model 777 
series airplanes. Since this wire bundle is located in a high-vibration 
area, chafing can lead to potential wire damage, and a short circuit 
could occur. These conditions, if not corrected, could result in wire 
damage leading to a short circuit, subsequent ignition of flammable 
vapors, and possible uncontrollable fire during fueling or flight.

Relevant Service Information

    We have reviewed Boeing Special Attention Service Bulletin 777-28-
0033, dated August 14, 2003. The service bulletin describes procedures 
for inspecting the valve control and indication wire bundles of the 
fuel system of the wing rear spar for discrepancies (chafing damage and 
incorrect routing), and corrective action if necessary. The corrective 
action involves repairing any damage and modifying the wire bundle 
routing, as applicable. Accomplishing the actions specified in the 
service information is intended to adequately address the unsafe 
condition.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other airplanes 
of this same type design. Therefore, we are proposing this AD, which 
would require accomplishing the actions specified in the service 
information described previously, except as discussed under 
``Difference Between the Proposed AD and Service Bulletin.''

Difference Between the Proposed AD and Service Bulletin

    The proposed AD identifies the correct part number (P/N) for a 
certain clamp for which an incorrect P/N was specified in the service 
bulletin. P/N BACC10GU105P, shown in the part list table of Kit 
005W3225 and in the step tables in Figures 3 and 4 of the 
Accomplishment Instructions of the service bulletin, is not a valid P/
N; the correct P/N is BACC10JU105P. The manufacturer is aware of this 
discrepancy, concurs with the change, and has issued Information Notice 
(IN) 777-28-0033 IN 01, dated January 29, 2004, to inform operators of 
the error. We have included this information in paragraph (f) of this 
proposed AD.

Clarification of Inspection Terminology

    In this proposed AD, the ``inspection'' of the wire bundles, as 
specified in the service bulletin is referred to as a ``detailed 
inspection.'' We have included the definition for a detailed inspection 
in a note in the proposed AD.

Costs of Compliance

    There are about 403 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 129 airplanes of 
U.S. registry. The proposed inspection would take about 1 work hour per 
airplane, at an average labor rate of $65 per work hour. Based on these 
figures, the estimated cost of the proposed inspection for U.S. 
operators is $8,385, or $65 per airplane.

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated 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 
proposed AD.

Regulatory Findings

    We have determined that this proposed AD will not have federalism 
implications under Executive Order 13132. This proposed 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. 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, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Boeing: Docket No. FAA-2005-20350; Directorate Identifier 2004-NM-
202--AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this AD action by April 1, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 777-200 and -300 series 
airplanes, certificated in any category; as identified in Boeing 
Special Attention Service Bulletin 777-28-0033, dated August 14, 
2003.

Unsafe Condition

    (d) This AD was prompted by reports of six incidents of the 
valve control and indication wire bundles of the fuel system chafing 
against the rear spar stiffeners outside the fuel tank. We are 
issuing this AD to prevent this chafing, which could result in wire 
damage leading to a short circuit, subsequent ignition of flammable 
vapors, and possible uncontrollable fire during fueling or flight.

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.

Detailed Inspection/Corrective Action

    (f) Within 18 months after the effective date of this AD: Do a 
detailed inspection of the valve control and indication wire bundles 
of the fuel system of the wing rear spar for discrepancies 
(including any applicable corrective action), by doing all the 
actions specified in the Accomplishment Instructions of Boeing 
Special Attention

[[Page 7683]]

Service Bulletin 777-28-0033, dated August 14, 2003. Any applicable 
corrective action must be done before further flight. Part number 
(P/N) BACC10GU105P, shown in the part list table of Kit 005W3225 and 
in the step tables in Figures 3 and 4 of the Accomplishment 
Instructions of the service bulletin, is not a valid P/N; the 
correct P/N that must be used is P/N BACC10JU105P.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Seattle Aircraft Certification Office, FAA, has 
the authority to approve AMOCs for this AD, if requested in 
accordance with the procedures found in 14 CFR 39.19.

    Issued in Renton, Washington, on February 6, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-2838 Filed 2-14-05; 8:45 am]
BILLING CODE 4910-13-P

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