Airworthiness Directives; Boeing Model 747-400 and 747-400D Series Airplanes, 40953-40955 [E8-15710]

Download as PDF Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations edge skin and fin for any cracking, corrosion, scratches, dents, creases, and/or buckling and repair as necessary. All non-transparent protective coatings and their adhesive must be removed for this inspection. (2) Within 100 hours time-in-service (TIS) after August 21, 2008 (the effective date of this AD), and repetitively thereafter at intervals not to exceed 100 hours TIS, perform a detailed inspection of the vertical stabilizer leading edge skin, leading edge, fin skin, and the fin forward attachment point for any cracking, corrosion, scratches, dents, creases, and/or buckling to include: (i) Inspection of the entire leading edge down to the forward attach fitting and removal of dorsal fin extensions if installed in order to inspect the obscured areas of the fin. (ii) Inspection of the fin skin for corrosion and cracks, paying particular attention to the center rib rivet holes and the skin joint at the fin base. (iii) Inspection of the fin forward attachment point for corrosion, removal of the fin tip, and inspection of the top rib for cracks at the skin stiffener cutouts. Manufacturer 40953 (3) If any damage is found during any inspection required in paragraph (f)(1) or (f)(2) of this AD, before further flight, obtain an FAA-approved repair scheme from the manufacturer and incorporate that repair. (4) The following transparent polyurethane protective tapes have been assessed as suitable for use to re-protect the leading edge and may remain in situ for subsequent inspections, provided they are sound and in a condition to permit visual inspection of the skin beneath them: Product (i) 3M ............................................... (ii) Scapa ......................................... 8591, or 8671, 8672 and 8681HS (aeronautical grade). Aeroshield P2604 (transparent). Related Information DEPARTMENT OF TRANSPORTATION (h) Refer to MCAI Civil Aviation Authority of New Zealand AD DCA/FU24/176C, dated September 27, 2007, for related information. Federal Aviation Administration FAA AD Differences Material Incorporated by Reference Note 2: This AD differs from the MCAI and/or service information as follows: (1) The inspections required in this AD must be performed by a person authorized under 14 CFR part 43 to perform inspections, as opposed to the MCAI, which allows the holder of a pilot license to perform the inspections. (2) The 50-hour inspection required in the MCAI goes away because the ‘‘before the first flight of each day’’ inspection captures the intent. rwilkins on PROD1PC63 with RULES Note 1: You may apply for an alternative method of compliance (AMOC) for an alternative to the transparent polyurethane protective tapes listed above. (i) You must use Chapter 05, page 25 of the FU–24–950 Series Maintenance Manual, issued December 1978, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Pacific Aerospace Limited, Hamilton Airport, Private Bag, 3027 Hamilton, New Zealand; telephone: +64 7– 843–6144; facsimile: +64 7–843–6134. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 Issued in Kansas City, Missouri, on June 30, 2008. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–16191 Filed 7–16–08; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2007–0267; Directorate Identifier 2007–NM–245–AD; Amendment 39–15609; AD 2008–14–14] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–400 and 747–400D Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747–400 and 747–400D series airplanes. This AD requires a general visual inspection of the power feeder wire bundle of the auxiliary power unit (APU) where it crosses the hydraulic system 4 return tube to determine if parts are installed to provide separation between the wire bundle and hydraulic tube. This AD also requires related investigative and corrective actions if necessary. This AD results from a report that the power feeder wire bundle of the APU was found touching the hydraulic system return tube during inspection of an airplane. We are issuing this AD to prevent insufficient clearance between the wire bundle and hydraulic tube that could lead to chafing of the wire bundle, which could cause arcing and a consequent hydraulic fluid fire in an area outside of the smoke detection and fire extinguishing zone; this condition could result in an uncontrolled fire on the airplane. DATES: This AD is effective August 21, 2008. The Director of the Federal Register approved the incorporation by reference E:\FR\FM\17JYR1.SGM 17JYR1 40954 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations of a certain publication listed in this AD as of August 21, 2008. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Examining the AD Docket You may examine the AD docket on the Internet at 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6482; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain Boeing Model 747–400 and 747– 400D series airplanes. That NPRM was published in the Federal Register on December 4, 2007 (72 FR 68106). That NPRM proposed to require a general visual inspection of the power feeder wire bundle of the auxiliary power unit (APU) where it crosses the hydraulic system 4 return tube to determine if parts are installed to provide separation between the wire bundle and hydraulic tube. That NPRM also proposed to require related investigative and corrective actions if necessary. Comments We gave the public the opportunity to participate in developing this AD. We considered the three comments received. rwilkins on PROD1PC63 with RULES Supportive Comment The commenters Adam W. Rocks and Boeing support the NPRM. Request To Revise Applicability Brady J. Mitchell, an employee of Boeing, requests that all Boeing Model 747–400 series airplanes converted from a passenger-to-freighter configuration be excluded from the applicability of the VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 NPRM. Mr. Mitchell states that those airplanes will have new hydraulic tubes and eliminate the possibility of an insufficient clearance or potential chafing condition between the tubes and the power feeder wire bundles of the APU between stations 2040 and 2060. Mr. Mitchell concludes that such a configuration change fulfills the requirements in paragraph (f) of the NPRM. We do not agree. We have reviewed the details of the passenger-to-freighter conversion to which the commenter refers. We have determined that there is not a common configuration for each airplane that is converted. Rather, the details of each conversion are likely to be different from airplane to airplane. Therefore, each conversion configuration needs to be evaluated to ensure the unsafe condition identified in this AD is corrected. For this reason, providing a blanket exception for all airplanes that are converted to a freighter configuration is not appropriate. However, anyone may apply for an alternative method of compliance (AMOC) for relief from the requirements of this AD. Under the provisions of paragraph (h) of this AD, we may consider requests for approval of an AMOC if sufficient data are submitted to substantiate that a passenger-to-freighter configuration change would provide an acceptable level of safety. 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. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed. List of Subjects in 14 CFR Part 39 Costs of Compliance There are about 462 airplanes of the affected design in the worldwide fleet. This AD affects 61 airplanes of U.S. registry. The required inspection takes 1 work hour per airplane, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $4,880, or $80 per airplane. I 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 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Regulatory Findings This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. You can find our regulatory evaluation and the estimated costs of compliance in the AD Docket. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–14–14 Boeing: Amendment 39–15609. Docket No. FAA–2007–0267; Directorate Identifier 2007–NM–245–AD. Effective Date (a) This airworthiness directive (AD) is effective August 21, 2008. Affected ADs (b) None. E:\FR\FM\17JYR1.SGM 17JYR1 Federal Register / Vol. 73, No. 138 / Thursday, July 17, 2008 / Rules and Regulations Applicability (c) This AD applies to Boeing Model 747– 400 and 747–400D series airplanes, certificated in any category; as identified in Boeing Special Attention Service Bulletin 747–24–2257, Revision 1, dated August 2, 2007. Unsafe Condition (d) This AD results from a report that the power feeder wire bundle of the auxiliary power unit (APU) was found touching the hydraulic system return tube during inspection of an airplane. We are issuing this AD to prevent insufficient clearance between the wire bundle and hydraulic tube that could lead to chafing of the wire bundle, which could cause arcing and a consequent hydraulic fluid fire in an area outside of the smoke detection and fire extinguishing zone; this condition could result in an uncontrolled fire on 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. Inspection and Related Investigative and Corrective Actions (f) Within 24 months after the effective date of this AD, do a general visual inspection of the power feeder wire bundle of the APU where it crosses the hydraulic system 4 return tube to determine if parts are installed to provide separation between the wire bundle and hydraulic tube, and do all the related investigative and corrective actions as applicable, by accomplishing all of the actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–24–2257, Revision 1, dated August 2, 2007. The related investigative and corrective actions must be accomplished before further flight after the inspection. rwilkins on PROD1PC63 with RULES Credit for Actions Done According to Previous Issue of Service Bulletin (g) Actions done before the effective date of this AD in accordance with Boeing Special Attention Service Bulletin 747–24–2257, dated May 18, 2006, are acceptable for compliance with the corresponding requirements of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (h)(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. Material Incorporated by Reference (i) You must use Boeing Special Attention Service Bulletin 747–24–2257, Revision 1, VerDate Aug<31>2005 18:28 Jul 16, 2008 Jkt 214001 dated August 2, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. (3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on June 27, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–15710 Filed 7–16–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0362; Directorate Identifier 2007–NM–308–AD; Amendment 39–15611; AD 2008–14–16] RIN 2120-AA64 Airworthiness Directives; 328 Support Services GmbH Dornier Model 328–100 and –300 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: At least one incident has occurred where, immediately after take-off, the passenger door of a Dornier 328 completely opened. * * * Substantial damage to the door, handrails, door hinge arms and fuselage skin were found. * * * Although final proof could not be obtained, the most likely way in which the door opened was that the door handle was PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 40955 inadvertently operated during the take-off run. * * * * * [T]his Airworthiness Directive (AD) aims to prevent further incidents of inadvertent opening and possible detachment of a passenger door in-flight, likely resulting in damage to airframe and systems and, under less favorable circumstances, loss of control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective August 21, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 21, 2008. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 27, 2008 (73 FR 16219). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: At least one incident has occurred where, immediately after take-off, the passenger door of a Dornier 328 completely opened. The flight crew reportedly had no cockpit indication or audible chime prior to this event. The aircraft returned to the departure airfield and made an uneventful emergency landing. Substantial damage to the door, handrails, door hinge arms and fuselage skin were found. The subsequent investigation could not find any deficiency in the design of the main cabin door locking mechanism. In addition, no technical failure could be determined that precipitated the event. The flight data recorder showed that the door was closed and locked before take-off and opened shortly afterward. Although final proof could not be obtained, the most likely way in which the door opened was that the door handle was inadvertently operated during the take-off run. In response to the incident, AvCraft (the TC (type certificate) holder at the time) E:\FR\FM\17JYR1.SGM 17JYR1

Agencies

[Federal Register Volume 73, Number 138 (Thursday, July 17, 2008)]
[Rules and Regulations]
[Pages 40953-40955]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-15710]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0267; Directorate Identifier 2007-NM-245-AD; 
Amendment 39-15609; AD 2008-14-14]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Boeing Model 747-400 and 747-400D series airplanes. This AD requires a 
general visual inspection of the power feeder wire bundle of the 
auxiliary power unit (APU) where it crosses the hydraulic system 4 
return tube to determine if parts are installed to provide separation 
between the wire bundle and hydraulic tube. This AD also requires 
related investigative and corrective actions if necessary. This AD 
results from a report that the power feeder wire bundle of the APU was 
found touching the hydraulic system return tube during inspection of an 
airplane. We are issuing this AD to prevent insufficient clearance 
between the wire bundle and hydraulic tube that could lead to chafing 
of the wire bundle, which could cause arcing and a consequent hydraulic 
fluid fire in an area outside of the smoke detection and fire 
extinguishing zone; this condition could result in an uncontrolled fire 
on the airplane.

DATES: This AD is effective August 21, 2008.
    The Director of the Federal Register approved the incorporation by 
reference

[[Page 40954]]

of a certain publication listed in this AD as of August 21, 2008.

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

Examining the AD Docket

    You may examine the AD docket on the Internet at 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Georgios Roussos, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6482; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
certain Boeing Model 747-400 and 747-400D series airplanes. That NPRM 
was published in the Federal Register on December 4, 2007 (72 FR 
68106). That NPRM proposed to require a general visual inspection of 
the power feeder wire bundle of the auxiliary power unit (APU) where it 
crosses the hydraulic system 4 return tube to determine if parts are 
installed to provide separation between the wire bundle and hydraulic 
tube. That NPRM also proposed to require related investigative and 
corrective actions if necessary.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the three comments received.

Supportive Comment

    The commenters Adam W. Rocks and Boeing support the NPRM.

Request To Revise Applicability

    Brady J. Mitchell, an employee of Boeing, requests that all Boeing 
Model 747-400 series airplanes converted from a passenger-to-freighter 
configuration be excluded from the applicability of the NPRM. Mr. 
Mitchell states that those airplanes will have new hydraulic tubes and 
eliminate the possibility of an insufficient clearance or potential 
chafing condition between the tubes and the power feeder wire bundles 
of the APU between stations 2040 and 2060. Mr. Mitchell concludes that 
such a configuration change fulfills the requirements in paragraph (f) 
of the NPRM.
    We do not agree. We have reviewed the details of the passenger-to-
freighter conversion to which the commenter refers. We have determined 
that there is not a common configuration for each airplane that is 
converted. Rather, the details of each conversion are likely to be 
different from airplane to airplane. Therefore, each conversion 
configuration needs to be evaluated to ensure the unsafe condition 
identified in this AD is corrected. For this reason, providing a 
blanket exception for all airplanes that are converted to a freighter 
configuration is not appropriate. However, anyone may apply for an 
alternative method of compliance (AMOC) for relief from the 
requirements of this AD. Under the provisions of paragraph (h) of this 
AD, we may consider requests for approval of an AMOC if sufficient data 
are submitted to substantiate that a passenger-to-freighter 
configuration change would provide an acceptable level of safety.

Conclusion

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

Costs of Compliance

    There are about 462 airplanes of the affected design in the 
worldwide fleet. This AD affects 61 airplanes of U.S. registry. The 
required inspection takes 1 work hour per airplane, at an average labor 
rate of $80 per work hour. Based on these figures, the estimated cost 
of the AD for U.S. operators is $4,880, or $80 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979), and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    You can find our regulatory evaluation and the estimated costs of 
compliance in the AD Docket.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-14-14 Boeing: Amendment 39-15609. Docket No. FAA-2007-0267; 
Directorate Identifier 2007-NM-245-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective August 21, 
2008.

Affected ADs

    (b) None.

[[Page 40955]]

Applicability

    (c) This AD applies to Boeing Model 747-400 and 747-400D series 
airplanes, certificated in any category; as identified in Boeing 
Special Attention Service Bulletin 747-24-2257, Revision 1, dated 
August 2, 2007.

Unsafe Condition

    (d) This AD results from a report that the power feeder wire 
bundle of the auxiliary power unit (APU) was found touching the 
hydraulic system return tube during inspection of an airplane. We 
are issuing this AD to prevent insufficient clearance between the 
wire bundle and hydraulic tube that could lead to chafing of the 
wire bundle, which could cause arcing and a consequent hydraulic 
fluid fire in an area outside of the smoke detection and fire 
extinguishing zone; this condition could result in an uncontrolled 
fire on 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.

Inspection and Related Investigative and Corrective Actions

    (f) Within 24 months after the effective date of this AD, do a 
general visual inspection of the power feeder wire bundle of the APU 
where it crosses the hydraulic system 4 return tube to determine if 
parts are installed to provide separation between the wire bundle 
and hydraulic tube, and do all the related investigative and 
corrective actions as applicable, by accomplishing all of the 
actions specified in the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-24-2257, Revision 1, dated 
August 2, 2007. The related investigative and corrective actions 
must be accomplished before further flight after the inspection.

Credit for Actions Done According to Previous Issue of Service Bulletin

    (g) Actions done before the effective date of this AD in 
accordance with Boeing Special Attention Service Bulletin 747-24-
2257, dated May 18, 2006, are acceptable for compliance with the 
corresponding requirements of paragraph (f) of this AD.

Alternative Methods of Compliance (AMOCs)

    (h)(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.

Material Incorporated by Reference

    (i) You must use Boeing Special Attention Service Bulletin 747-
24-2257, Revision 1, dated August 2, 2007, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 
98124-2207.
    (3) You may review copies of the service information 
incorporated by reference at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: http://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.

    Issued in Renton, Washington, on June 27, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E8-15710 Filed 7-16-08; 8:45 am]
BILLING CODE 4910-13-P