Airworthiness Directives; Boeing Model 757 Series Airplanes, 68764-68766 [E7-23639]

Download as PDF 68764 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules sroberts on PROD1PC70 with PROPOSALS and expertise. Membership on the steering committee will be limited to facilitate discussions. Priority will be given to those applicants representing an identified part of the aviation community who are empowered to speak for those interests. Additional participation is provided through the specialized work groups. At this time, the FAA is considering the establishment of work groups comprised of subject matter experts in the following subject areas: —14 CFR Part 25; Airplane Certification Takeoff and Landing Performance —14 CFR Part 23; Airplane Certification Takeoff and Landing Performance —14 CFR Part 121; Operations and training associated with takeoff and landing performance —14 CFR Parts 135, 125, and 91 Subpart K; Operations and training associated with takeoff and landing performance —14 CFR 139; Airport Certification and Operations —Current and new technologies for reporting and disseminating aircraft stopping capabilities on contaminated runways —Other work groups may be established if required. All non-government representatives serve without government compensation and bear all costs related to their participation on the steering committee or work groups. Members and participants should be available to attend all scheduled committee or work group meetings for the duration of the review. Make your request to participate on the steering committee or specialized work groups in writing on or before January 7, 2008. If wishing to participate on the Takeoff/Landing Performance Assessment Aviation Rulemaking Committee or its workgroups, please provide the following information (preferably by e-mail): Name: Title: Segment(s) of the industry or organization /association you represent: Organization Representing: Address: E-mail address: Telephone contact information: Specific area(s) of the committee in which you are interested in participating: Description of your education, technical background, and/or work experience in the area of the committee in which you would like to participate: Number of hours you will be available to participate in committee work per month in the first 90 days of the committee; in the first year; and beyond the first year, if necessary; and Number of days per month that you are available and have the financial capability to travel for committee activities. VerDate Aug<31>2005 18:18 Dec 05, 2007 Jkt 214001 The FAA will notify all selected members and participants in writing in advance of the first meeting. Comments. As noted above, persons wishing to comment on this subject may do so until February 4, 2008. In order to provide information to the committee, the FAA requests that commenters be timely in their comments. Commenters should be as specific as possible and provide as much detail in comments as necessary to facilitate regulatory decision making. Comments should address the specific section of the regulation at issue, a detailed explanation of what needs to be changed and why, and the proposed regulatory change. Information on costs and benefits of the proposed change are particularly helpful. Comments provided in response to this notice will assist the FAA and committee in their review and deliberation. Pamela Hamilton-Powell, Director, Office of Rulemaking. [FR Doc. E7–23740 Filed 12–5–07; 8:45 am] BILLING CODE 4910–13–P proposing this AD to prevent improperly sealed fasteners in the main and center fuel tanks from becoming an ignition source, in the event of a fault current, which could result in a fuel tank explosion and consequent loss of the airplane. DATES: We must receive comments on this proposed AD by January 22, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. DEPARTMENT OF TRANSPORTATION Examining the AD Docket Federal Aviation Administration You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Judy Coyle, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6497; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: 14 CFR Part 39 [Docket No. FAA–2007–0289; Directorate Identifier 2007–NM–208–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 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 757 series airplanes. This proposed AD would require sealing the fasteners on the front and rear spars inside the left and right main fuel tanks and on the lower panel of the center fuel tank. This proposed AD would also require inspections of the wire bundle support installations to verify if certain clamps are installed and if Teflon sleeving covers the wire bundles inside the left and right equipment cooling system bays, on the left and right rear spars, and on the left and right front spars; and corrective actions if necessary. This proposed AD results from a fuel system review conducted by the manufacturer. We are PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0289; Directorate Identifier 2007–NM–208–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will E:\FR\FM\06DEP1.SGM 06DEP1 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules sroberts on PROD1PC70 with PROPOSALS consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The FAA has examined the underlying safety issues involved in fuel tank explosions on several large transport airplanes, including the adequacy of existing regulations, the service history of airplanes subject to those regulations, and existing maintenance practices for fuel tank systems. As a result of those findings, we issued a regulation titled ‘‘Transport Airplane Fuel Tank System Design Review, Flammability Reduction and Maintenance and Inspection Requirements’’ (66 FR 23086, May 7, 2001). In addition to new airworthiness standards for transport airplanes and new maintenance requirements, this rule included Special Federal Aviation Regulation No. 88 (‘‘SFAR 88,’’ Amendment 21–78, and subsequent Amendments 21–82 and 21–83). Among other actions, SFAR 88 requires certain type design (i.e., type certificate (TC) and supplemental type certificate (STC)) holders to substantiate that their fuel tank systems can prevent ignition sources in the fuel tanks. This requirement applies to type design holders for large turbine-powered transport airplanes and for subsequent modifications to those airplanes. It requires them to perform design reviews and to develop design changes and maintenance procedures if their designs do not meet the new fuel tank safety standards. As explained in the preamble to the rule, we intended to adopt airworthiness directives to mandate any changes found necessary to address unsafe conditions identified as a result of these reviews. In evaluating these design reviews, we have established four criteria intended to define the unsafe conditions associated with fuel tank systems that require corrective actions. The percentage of operating time during which fuel tanks are exposed to flammable conditions is one of these criteria. The other three criteria address the failure types under evaluation: Single failures, single failures in combination with a latent condition(s), and in-service failure experience. For all four criteria, the evaluations included consideration of previous actions taken VerDate Aug<31>2005 18:18 Dec 05, 2007 Jkt 214001 that may mitigate the need for further action. We have determined that the actions identified in this proposed AD are necessary to reduce the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane. Boeing has found that it is possible for some fuel tank fasteners, in the event of a fault current, to become an ignition source on Boeing Model 757 series airplanes. This condition, if not corrected, could result in a fuel tank explosion and consequent loss of the airplane. Relevant Service Information We have reviewed Boeing Alert Service Bulletin 757–57A0064, dated July 16, 2007. The service bulletin describes procedures for sealing the fasteners on the front and rear spars inside the left and right main fuel tanks and sealing the fasteners on the lower panel of the center fuel tank. The service bulletin also describes procedures for doing general visual inspections of the wire bundle support installations to verify if certain full cushion clamps are installed and to confirm if the wire bundles are covered in Teflon sleeving at the following locations: Inside the left and right equipment cooling system bays, on the left and right rear spars, and on the left and right front spars. The service bulletin also describes procedures for doing corrective actions if necessary, which include replacing any incorrect clamps with certain full cushion clamps and installing any missing Teflon sleeving. 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. For this reason, 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 compliance table in paragraph 1.E. of the service bulletin recommends accomplishing the corrective actions (clamp replacement and installation of PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 68765 Teflon sleeving) within 5 years of the date on the service bulletin. This AD, however, would require accomplishing the corrective actions, if necessary, before further flight after accomplishing the inspections. We have coordinated this difference with Boeing. Costs of Compliance There are about 1,049 airplanes of the affected design in the worldwide fleet. This proposed AD would affect about 539 airplanes of U.S. registry. The proposed actions would take up to 545 work hours per airplane depending on the airplane configuration, at an average labor rate of $80 per work hour. Required parts would cost about $325 per airplane. Based on these figures, the estimated cost of the proposed AD for U.S. operators is up to $23,675,575, or up to $43,925 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify 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 E:\FR\FM\06DEP1.SGM 06DEP1 68766 Federal Register / Vol. 72, No. 234 / Thursday, December 6, 2007 / Proposed Rules under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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 Alternative Methods of Compliance (AMOCs) (g)(1) 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. (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. Issued in Renton, Washington, on November 23, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23639 Filed 12–5–07; 8:45 am] BILLING CODE 4910–13–P [Amended] DEPARTMENT OF TRANSPORTATION 2. The Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Federal Aviation Administration Boeing: Docket No. FAA–2007–0289; Directorate Identifier 2007–NM–208–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 22, 2008. Unsafe Condition (d) This AD results from a fuel system review conducted by the manufacturer. We are issuing this AD to prevent improperly sealed fasteners in the main and center fuel tanks from becoming an ignition source, in the event of a fault current, which could result in a fuel tank explosion and consequent loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Fastener Sealing and Inspections (f) Within 60 months after the effective date of this AD, seal the applicable fasteners and do the general visual inspections of the wire bundle support installations, and do all the applicable corrective actions before further flight, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Boeing Alert 18:18 Dec 05, 2007 Jkt 214001 [Docket No. FAA–2007–0284; Directorate Identifier 2004–SW–06–AD] Airworthiness Directives; Sikorsky Aircraft Corporation Model S–61A, S– 61D, S–61E, and S–61V Helicopters Applicability (c) This AD applies to Boeing Model 757– 200, –200CB, –200PF, and –300 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 757–57A0064, dated July 16, 2007. VerDate Aug<31>2005 14 CFR Part 39 RIN 2120–AA64 Affected ADs (b) None. sroberts on PROD1PC70 with PROPOSALS Service Bulletin 757–57A0064, dated July 16, 2007. Federal Aviation Administration, DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: This document proposes adopting a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters. The AD would require installing an electric chip detector on each engine and an on-board chip detector annunciation system. The AD would also require revising the Rotorcraft Flight Manual (RFM) to add procedures for crew response to the illumination of an on-board chip detector warning light. This AD would also require testing the engine chip detector system at specified intervals. This proposal is prompted by reports of Number 5 engine bearing failures. Failure of the bearing resulted in erratic movement of the high-speed, engine-totransmission shaft (shaft), an oil leak, an in-flight fire, and an emergency landing. The actions specified by the proposed AD are intended to detect an impending bearing failure, which if undetected and PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 not addressed by appropriate crew action may result in an oil leak, a severed shaft housing, an uncontained in-flight fire, and a subsequent emergency landing. DATES: Comments must be received on or before February 4, 2008. ADDRESSES: Use one of the following addresses to submit comments on this proposed AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. You may get the service information identified in this proposed AD from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, Connecticut, phone (203) 383–4866, e-mail address tsslibrary@sikorsky.com. You may examine the comments to this proposed AD in the AD docket on the Internet at http:// www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft Certification Office, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7190, fax (781) 238–7170. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption ADDRESSES. Include the docket number ‘‘FAA–2007–0284, Directorate Identifier 2004–SW–06–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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each E:\FR\FM\06DEP1.SGM 06DEP1

Agencies

[Federal Register Volume 72, Number 234 (Thursday, December 6, 2007)]
[Proposed Rules]
[Pages 68764-68766]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23639]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0289; Directorate Identifier 2007-NM-208-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757 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 757 series airplanes. This proposed AD would 
require sealing the fasteners on the front and rear spars inside the 
left and right main fuel tanks and on the lower panel of the center 
fuel tank. This proposed AD would also require inspections of the wire 
bundle support installations to verify if certain clamps are installed 
and if Teflon sleeving covers the wire bundles inside the left and 
right equipment cooling system bays, on the left and right rear spars, 
and on the left and right front spars; and corrective actions if 
necessary. This proposed AD results from a fuel system review conducted 
by the manufacturer. We are proposing this AD to prevent improperly 
sealed fasteners in the main and center fuel tanks from becoming an 
ignition source, in the event of a fault current, which could result in 
a fuel tank explosion and consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by January 22, 
2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this 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 http://
www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) is in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

FOR FURTHER INFORMATION CONTACT: Judy Coyle, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6497; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0289; 
Directorate Identifier 2007-NM-208-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will

[[Page 68765]]

consider all comments received by the closing date and may amend this 
proposed AD because of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The FAA has examined the underlying safety issues involved in fuel 
tank explosions on several large transport airplanes, including the 
adequacy of existing regulations, the service history of airplanes 
subject to those regulations, and existing maintenance practices for 
fuel tank systems. As a result of those findings, we issued a 
regulation titled ``Transport Airplane Fuel Tank System Design Review, 
Flammability Reduction and Maintenance and Inspection Requirements'' 
(66 FR 23086, May 7, 2001). In addition to new airworthiness standards 
for transport airplanes and new maintenance requirements, this rule 
included Special Federal Aviation Regulation No. 88 (``SFAR 88,'' 
Amendment 21-78, and subsequent Amendments 21-82 and 21-83).
    Among other actions, SFAR 88 requires certain type design (i.e., 
type certificate (TC) and supplemental type certificate (STC)) holders 
to substantiate that their fuel tank systems can prevent ignition 
sources in the fuel tanks. This requirement applies to type design 
holders for large turbine-powered transport airplanes and for 
subsequent modifications to those airplanes. It requires them to 
perform design reviews and to develop design changes and maintenance 
procedures if their designs do not meet the new fuel tank safety 
standards. As explained in the preamble to the rule, we intended to 
adopt airworthiness directives to mandate any changes found necessary 
to address unsafe conditions identified as a result of these reviews.
    In evaluating these design reviews, we have established four 
criteria intended to define the unsafe conditions associated with fuel 
tank systems that require corrective actions. The percentage of 
operating time during which fuel tanks are exposed to flammable 
conditions is one of these criteria. The other three criteria address 
the failure types under evaluation: Single failures, single failures in 
combination with a latent condition(s), and in-service failure 
experience. For all four criteria, the evaluations included 
consideration of previous actions taken that may mitigate the need for 
further action.
    We have determined that the actions identified in this proposed AD 
are necessary to reduce the potential of ignition sources inside fuel 
tanks, which, in combination with flammable fuel vapors, could result 
in fuel tank explosions and consequent loss of the airplane.
    Boeing has found that it is possible for some fuel tank fasteners, 
in the event of a fault current, to become an ignition source on Boeing 
Model 757 series airplanes. This condition, if not corrected, could 
result in a fuel tank explosion and consequent loss of the airplane.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 757-57A0064, dated 
July 16, 2007. The service bulletin describes procedures for sealing 
the fasteners on the front and rear spars inside the left and right 
main fuel tanks and sealing the fasteners on the lower panel of the 
center fuel tank. The service bulletin also describes procedures for 
doing general visual inspections of the wire bundle support 
installations to verify if certain full cushion clamps are installed 
and to confirm if the wire bundles are covered in Teflon sleeving at 
the following locations: Inside the left and right equipment cooling 
system bays, on the left and right rear spars, and on the left and 
right front spars. The service bulletin also describes procedures for 
doing corrective actions if necessary, which include replacing any 
incorrect clamps with certain full cushion clamps and installing any 
missing Teflon sleeving. 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. For this reason, 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 compliance table in paragraph 1.E. of the service bulletin 
recommends accomplishing the corrective actions (clamp replacement and 
installation of Teflon sleeving) within 5 years of the date on the 
service bulletin. This AD, however, would require accomplishing the 
corrective actions, if necessary, before further flight after 
accomplishing the inspections. We have coordinated this difference with 
Boeing.

Costs of Compliance

    There are about 1,049 airplanes of the affected design in the 
worldwide fleet. This proposed AD would affect about 539 airplanes of 
U.S. registry. The proposed actions would take up to 545 work hours per 
airplane depending on the airplane configuration, at an average labor 
rate of $80 per work hour. Required parts would cost about $325 per 
airplane. Based on these figures, the estimated cost of the proposed AD 
for U.S. operators is up to $23,675,575, or up to $43,925 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify 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

[[Page 68766]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Boeing: Docket No. FAA-2007-0289; Directorate Identifier 2007-NM-
208-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by January 
22, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 757-200, -200CB, -200PF, and 
-300 series airplanes, certificated in any category; as identified 
in Boeing Alert Service Bulletin 757-57A0064, dated July 16, 2007.

Unsafe Condition

    (d) This AD results from a fuel system review conducted by the 
manufacturer. We are issuing this AD to prevent improperly sealed 
fasteners in the main and center fuel tanks from becoming an 
ignition source, in the event of a fault current, which could result 
in a fuel tank explosion and consequent loss of the airplane.

Compliance

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

Fastener Sealing and Inspections

    (f) Within 60 months after the effective date of this AD, seal 
the applicable fasteners and do the general visual inspections of 
the wire bundle support installations, and do all the applicable 
corrective actions before further flight, by accomplishing all of 
the applicable actions specified in the Accomplishment Instructions 
of Boeing Alert Service Bulletin 757-57A0064, dated July 16, 2007.

Alternative Methods of Compliance (AMOCs)

    (g)(1) 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.
    (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.

    Issued in Renton, Washington, on November 23, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E7-23639 Filed 12-5-07; 8:45 am]
BILLING CODE 4910-13-P