Airworthiness Directives; Boeing Model 747-400, -400D, and -400F Series Airplanes, 32248-32250 [E8-12725]

Download as PDF 32248 Federal Register / Vol. 73, No. 110 / Friday, June 6, 2008 / Proposed Rules 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 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 this 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. 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, 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 AD: Boeing: Docket No. FAA–2008–0612; Directorate Identifier 2008–NM–059–AD. dwashington3 on PRODPC61 with PROPOSALS Comments Due Date (a) We must receive comments by July 21, 2008. Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category. VerDate Aug<31>2005 11:59 Jun 05, 2008 Jkt 214001 Unsafe Condition (d) This AD results from a report of a crack found in the right-side Stringer 11 longeron horizontal flange, adjacent to the horizontal stabilizer pivot bulkhead, during a routine maintenance inspection. We are issuing this AD to detect and correct fatigue cracking of the longeron, which can propagate and cause damage to the adjacent horizontal stabilizer pivot bulkhead. This damage could result in loss of structural integrity and consequent inability of the bulkhead to carry flight loads, which could adversely affect controllability of the airplane. Compliance (e) Comply with this AD within the compliance times specified, unless already done. Inspection/Related Investigative and Corrective Actions (f) Except as provided by paragraph (g) of this AD: At the applicable times specified in paragraph 1.E. of Boeing Alert Service Bulletin 747–53A2703, dated February 14, 2008, do a surface high frequency eddy current (HFEC) inspection for cracks in the left- and right-side Stringer 11 longeron exposed surfaces and edges between Station 2598 and 2607 adjacent to the horizontal stabilizer pivot bulkhead; and do all applicable related investigative and corrective actions before further flight, in accordance with the Accomplishment Instructions of the service bulletin, except as provided by paragraph (h) of this AD. Exception to Compliance Times (g) Where Boeing Alert Service Bulletin 747–53A2703, dated February 14, 2008, 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 crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2703, dated February 14, 2008, specifies to contact Boeing for appropriate action: Before further flight, repair 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: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6437; 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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 (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. Issued in Renton, Washington, on May 29, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–12712 Filed 6–5–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0620; Directorate Identifier 2007–NM–357–AD] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400, –400D, and –400F Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain Boeing Model 747–400, –400D, and –400F series airplanes. This proposed AD would require performing repetitive operational tests of the engine fuel suction feed of the fuel system, and other related testing if necessary. This proposed AD results from a report of inservice occurrences of loss of fuel system suction feed capability, followed by total loss of pressure of the fuel feed system. We are proposing this AD to detect and correct failure of the engine fuel suction feed of the fuel system, which could result in multi-engine flameout, inability to restart the engines, and consequent forced landing of the airplane. DATES: We must receive comments on this proposed AD by July 21, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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. E:\FR\FM\06JNP1.SGM 06JNP1 Federal Register / Vol. 73, No. 110 / Friday, June 6, 2008 / Proposed Rules • 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 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 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: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6438; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Comments Invited dwashington3 on PRODPC61 with PROPOSALS 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–2008–0620; Directorate Identifier 2007–NM–357–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 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 https:// 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 We have received a report of inservice occurrences of loss of fuel system suction feed capability, followed by total loss of pressure of the fuel feed system. This condition, if not corrected, could result in multi-engine flameout, inability to restart the engines, and VerDate Aug<31>2005 11:59 Jun 05, 2008 Jkt 214001 consequent forced landing of the airplane. FAA’s Conclusions We have determined that it is necessary to require an operational test of the engine fuel suction feed of the fuel system, and other related testing, as applicable. Procedures for doing the operational test can be found in the maintenance manual. The other related testing is for airplanes on which deterioration in the engine RPM is found on one or both of the engines during the operational test. Failure of the engine fuel suction feed of the fuel system could result in the unsafe condition described previously. FAA’s Determination and Requirements of This Proposed AD We are proposing this AD because 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. This proposed AD would require performing repetitive operational tests of the engine fuel suction feed of the fuel system, and other related testing if necessary. Costs of Compliance We estimate that this proposed AD would affect 79 airplanes of U.S. registry. We also estimate that it would take 1 work-hour per product, per test, to comply with this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this proposed AD to the U.S. operators to be $6,320, or $80 per product, per test. 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. PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 32249 Regulatory Findings We 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 this 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. 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, 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 AD: Boeing: Docket No. FAA–2008–0620; Directorate Identifier 2007–NM–357–AD. Comments Due Date (a) We must receive comments by July 21, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747 –400, –400D, and –400F series airplanes, certificated in any category. Unsafe Condition (d) This AD results from a report of inservice occurrences of loss of fuel system suction feed capability, followed by total loss of pressure of the fuel feed system. We are issuing this AD to detect and correct failure of the engine fuel suction feed of the fuel system, which could result in multi-engine flameout, inability to restart the engines, and consequent forced landing of the airplane. E:\FR\FM\06JNP1.SGM 06JNP1 32250 Federal Register / Vol. 73, No. 110 / Friday, June 6, 2008 / Proposed Rules Compliance (e) Comply with this AD within the compliance times specified, unless already done. Operational Test/Other Related Testing (f) Within 30,000 flight hours after the effective date of this AD, perform an operational test of the engine fuel suction feed of the fuel system, and perform all other related testing, as applicable, before further flight, according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. One approved method is the operational test in Section 28–22–00, titled ‘‘Engine Fuel Feed System—Description and Operation,’’ of the Boeing 747 Aircraft Maintenance Manual; and Boeing 747–400 Task Card 28–022–04–01, titled ‘‘Operationally Check the Engine Fuel Suction Feed System,’’ dated June 18, 2007. Repeat the operational test thereafter at intervals not to exceed 30,000 flight hours. Thereafter, except as provided in paragraph (g) of this AD, no alternative procedure or repeat test intervals will be allowed. SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. One operator experienced failures of four Fuel Level Sensor-Amplifier (FLSA) and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been identified as having been caused by incorrect connector sleeves material fitted to the MTI units. Degradation of the electrical insulation sleeves of the Low-level indication lamps on the MTI on the flight deck can cause a short circuit that might result in high voltage being conveyed to the high- and low-level sensors in the outer tanks. This might cause the level sensor to heat above acceptable limits. 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–2008–0613; Directorate Identifier 2008–NM–066–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 consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// 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. * * * * * DEPARTMENT OF TRANSPORTATION This action is necessary to prevent overheating of the fuel level sensors, which could result in a fuel tank explosion and consequent loss of the airplane. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by July 7, 2008. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office 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 Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle ACO, FAA, ATTN: Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 917–6438; 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. Issued in Renton, Washington, on May 16, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–12725 Filed 6–5–08; 8:45 am] BILLING CODE 4910–13–P [Docket No. FAA–2008–0613; Directorate Identifier 2008–NM–066–AD] dwashington3 on PRODPC61 with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Airbus Model A300–600 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Aug<31>2005 11:59 Jun 05, 2008 Jkt 214001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 SUPPLEMENTARY INFORMATION: Comments Invited Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued Airworthiness Directive 2008–0055, dated March 5, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: One operator experienced failures of four Fuel Level Sensor-Amplifier (FLSA) and Multi Tank Indicators (MTI) units. FLSA and MTI failures have been identified as having been caused by incorrect connector sleeves material fitted to the MTI units. Degradation of the electrical insulation sleeves of the Low-level indication lamps on the MTI on the flight deck can cause a short circuit that might result in high voltage being conveyed to the high- and low-level sensors in the outer tanks. This might cause the level sensor to heat above acceptable limits. For the reasons stated above, this Airworthiness Directive (AD) requires the accomplishment of wiring modifications to protect the FLSA and the Flight Warning Computers from 115V AC and 28V DC short circuits within the MTI. This action is necessary to prevent overheating of the fuel level sensors, which could result in a fuel tank explosion and consequent loss of the airplane. You may obtain further information by examining the MCAI in the AD docket. E:\FR\FM\06JNP1.SGM 06JNP1

Agencies

[Federal Register Volume 73, Number 110 (Friday, June 6, 2008)]
[Proposed Rules]
[Pages 32248-32250]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-12725]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0620; Directorate Identifier 2007-NM-357-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-400, -400D, and -400F 
Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Boeing Model 747-400, -400D, and -400F series airplanes. This 
proposed AD would require performing repetitive operational tests of 
the engine fuel suction feed of the fuel system, and other related 
testing if necessary. This proposed AD results from a report of in-
service occurrences of loss of fuel system suction feed capability, 
followed by total loss of pressure of the fuel feed system. We are 
proposing this AD to detect and correct failure of the engine fuel 
suction feed of the fuel system, which could result in multi-engine 
flameout, inability to restart the engines, and consequent forced 
landing of the airplane.

DATES: We must receive comments on this proposed AD by July 21, 2008.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
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.

[[Page 32249]]

     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 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 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: Sue Lucier, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification 
Office, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 917-6438; 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-2008-0620; 
Directorate Identifier 2007-NM-357-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 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 https://
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

    We have received a report of in-service occurrences of loss of fuel 
system suction feed capability, followed by total loss of pressure of 
the fuel feed system. This condition, if not corrected, could result in 
multi-engine flameout, inability to restart the engines, and consequent 
forced landing of the airplane.

FAA's Conclusions

    We have determined that it is necessary to require an operational 
test of the engine fuel suction feed of the fuel system, and other 
related testing, as applicable. Procedures for doing the operational 
test can be found in the maintenance manual. The other related testing 
is for airplanes on which deterioration in the engine RPM is found on 
one or both of the engines during the operational test. Failure of the 
engine fuel suction feed of the fuel system could result in the unsafe 
condition described previously.

FAA's Determination and Requirements of This Proposed AD

    We are proposing this AD because 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. This proposed 
AD would require performing repetitive operational tests of the engine 
fuel suction feed of the fuel system, and other related testing if 
necessary.

Costs of Compliance

    We estimate that this proposed AD would affect 79 airplanes of U.S. 
registry. We also estimate that it would take 1 work-hour per product, 
per test, to comply with this proposed AD. The average labor rate is 
$80 per work-hour. Based on these figures, we estimate the cost of this 
proposed AD to the U.S. operators to be $6,320, or $80 per product, per 
test.

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 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 this 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.
    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, 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 AD:

Boeing: Docket No. FAA-2008-0620; Directorate Identifier 2007-NM-
357-AD.

Comments Due Date

    (a) We must receive comments by July 21, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747 -400, -400D, and -400F 
series airplanes, certificated in any category.

Unsafe Condition

    (d) This AD results from a report of in-service occurrences of 
loss of fuel system suction feed capability, followed by total loss 
of pressure of the fuel feed system. We are issuing this AD to 
detect and correct failure of the engine fuel suction feed of the 
fuel system, which could result in multi-engine flameout, inability 
to restart the engines, and consequent forced landing of the 
airplane.

[[Page 32250]]

Compliance

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

Operational Test/Other Related Testing

    (f) Within 30,000 flight hours after the effective date of this 
AD, perform an operational test of the engine fuel suction feed of 
the fuel system, and perform all other related testing, as 
applicable, before further flight, according to a method approved by 
the Manager, Seattle Aircraft Certification Office (ACO), FAA. One 
approved method is the operational test in Section 28-22-00, titled 
``Engine Fuel Feed System--Description and Operation,'' of the 
Boeing 747 Aircraft Maintenance Manual; and Boeing 747-400 Task Card 
28-022-04-01, titled ``Operationally Check the Engine Fuel Suction 
Feed System,'' dated June 18, 2007. Repeat the operational test 
thereafter at intervals not to exceed 30,000 flight hours. 
Thereafter, except as provided in paragraph (g) of this AD, no 
alternative procedure or repeat test intervals will be allowed.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Seattle ACO, FAA, ATTN: Sue Lucier, 
Aerospace Engineer, Propulsion Branch, ANM-140S, 1601 Lind Avenue, 
SW., Renton, Washington 98057-3356; telephone (425) 917-6438; 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.

    Issued in Renton, Washington, on May 16, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-12725 Filed 6-5-08; 8:45 am]
BILLING CODE 4910-13-P
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