Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-200F, 747-300, and 747SR Series Airplanes Equipped With General Electric (GE) CF6-45 or -50 Series Engines, 13347-13349 [05-5298]

Download as PDF Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations Unsafe Condition (d) This AD was prompted by reports of cracking of a certain bracket that attaches the flight deck instrument panel to the airplane structure. We are issuing this AD to detect and correct a cracked bracket. Failure of this bracket, combined with failure of the horizontal beam, could result in collapse of the left part of the flight deck instrument panel, and consequent reduced controllability 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. Service Bulletin Reference (f) The term ‘‘service bulletin,’’ as used in this AD, means the Accomplishment Instructions of Airbus Service Bulletins A330–25–3227 (for Model A330 series airplanes); and A340–25–4230 (for Model A340–200 and –300 series airplanes); both including Appendix 01; and both dated June 17, 2004; as applicable. Initial Inspection (g) At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, perform a detailed inspection of the bracket having part number (P/N) F2511012920000, which attaches the flight deck instrument panel to airplane structure, in accordance with the service bulletin. (1) For Model A330 series airplanes: Prior to the accumulation of 16,500 total flight cycles, or within 60 days after the effective date of this AD, whichever is later. (2) For Model A340–200 and –300 series airplanes: Prior to the accumulation of 9,700 total flight cycles, or within 2,700 flight cycles after the effective date of this AD, whichever is later. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.’’ No Cracking/Repetitive Inspections (h) If no cracking is found during the initial inspection required by paragraph (g) of this AD: Repeat the inspection thereafter at the applicable interval specified in paragraph (h)(1) or (h)(2) of this AD. (1) For Model A330 series airplanes: Intervals not to exceed 13,800 flight cycles. (2) For Model A340–200 and –300 series airplanes: Intervals not to exceed 7,000 flight cycles. Crack Found/Replacement, Reporting, and Repetitive Inspections (i) If any cracking is found during any inspection required by paragraph (g) or (h) of this AD: Do the actions in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, except as provided by paragraph (j) of this AD. VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 (1) Before further flight: Replace the cracked bracket with a new, improved bracket having P/N F2511012920095, in accordance with the service bulletin. (2) Within 30 days after performing the inspection, or within 30 days after the effective date of this AD, whichever is later: Report the cracked fitting to Airbus, Department AI/SE–A21, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. The report must include the airplane serial number, the number of flight cycles and flight hours on the airplane, the date of the inspection, and whether both flanges of a bracket are broken. Submitting Appendix 01 of the applicable service bulletin is acceptable for compliance with this paragraph. Under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120–0056. (3) Inspect the replaced bracket at the time specified in paragraph (i)(3)(i) or (i)(3)(ii) of this AD. Then, do repetitive inspections or replace the bracket as specified in paragraph (h) or (i) of this AD, as applicable. (i) For Model A330 series airplanes: Within 16,500 flight cycles after replacing the bracket. (ii) For Model A340–200 and –300 series airplanes: Within 9,700 flight cycles after replacing the bracket. (j) If both flanges of a bracket are broken: Before further flight, replace the bracket as specified in paragraph (i)(1) and perform any applicable related investigative and corrective actions (which may include inspections for damage to surrounding structure caused by the broken bracket, and corrective actions for any damage that is found), in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane ´ ´ Directorate, FAA; or the Direction Generale de l’Aviation Civile (DGAC) (or its delegated agent). Alternative Methods of Compliance (AMOCs) (k) The Manager, International Branch, ANM–116, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Related Information (l) French airworthiness directives F– 2004–140 and F–2004–141, both dated August 18, 2004, also address the subject of this AD. Material Incorporated by Reference (m) You must use Airbus Service Bulletin A330–25–3227, including Appendix 01, dated June 17, 2004; or Airbus Service Bulletin A340–25–4230, including Appendix 01, dated June 17, 2004; as applicable; to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Airbus, 1 Rond PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 13347 Point Maurice Bellonte, 31707 Blagnac Cedex, France. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW, room PL–401, Nassif Building, Washington, DC. Issued in Renton, Washington, on March 8, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–5297 Filed 3–18–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19945; Directorate Identifier 2004–NM–22–AD; Amendment 39– 14017; AD 2005–06–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–200B, 747–200C, 747–200F, 747–300, and 747SR Series Airplanes Equipped With General Electric (GE) CF6–45 or –50 Series Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747–200B, 747–200C, 747–200F, 747–300, and 747SR series airplanes, equipped with GE CF6–45 or –50 series engines. This AD requires modifying the side cowl assemblies on the engines by replacing existing wear plates with new extended wear plates and installing new stop fittings. This AD is prompted by reports of a gap at the interface of the lower portion of the side cowl and the aft flange of the thrust reverser. We are issuing this AD to prevent an excessive quantity of air from entering the fire zone that surrounds the engine, which, in the event of an engine fire, could result in an inability to control or extinguish the fire. DATES: This AD becomes effective April 25, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of April 25, 2005. ADDRESSES: For service information identified in this AD, contact Boeing E:\FR\FM\21MRR1.SGM 21MRR1 13348 Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2004–19945; the directorate identifier for this docket is 2004–NM– 22–AD. Dan Kinney, Aerospace Engineer, Propulsion FOR FURTHER INFORMATION CONTACT: Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6499; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with an AD for certain Boeing Model 747– 200B, 747–200C, 747–200F, 747–300, and 747SR series airplanes, equipped with General Electric CF6–45 or –50 series engines. That action, published in the Federal Register on January 3, 2005 (70 FR 51), proposed to require modifying the side cowl assemblies on the engines by replacing existing wear plates with new extended wear plates and installing new stop fittings. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the single comment that has been submitted on the proposed AD. The commenter supports the proposed AD. Conclusion We have carefully reviewed the available data, including the comment that has been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 140 airplanes of the affected design in the worldwide fleet. This AD affects about 38 airplanes of U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours Average labor rate per hour Parts Cost per airplane Fleet cost Modification per Boeing Service Bulletin 747–71–2300, Revision 1 ............... 72 $65 $25,736 $30,416 $1,155,808 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 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: VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 (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. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. 2005–06–09 Boeing: Amendment 39–14017. Docket No. FAA–2004–19945; Directorate Identifier 2004–NM–22–AD. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Unsafe Condition (d) This AD was prompted by reports of a gap at the interface of the lower portion of the side cowl and the aft flange of the thrust reverser. We are issuing this AD to prevent an excessive quantity of air from entering the fire zone that surrounds the engine, which, in the event of an engine fire, could result in an inability to control or extinguish the fire. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 Effective Date (a) This AD becomes effective April 25, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 200B, 747–200C, 747–200F, 747–300, and 747SR series airplanes; certificated in any category; equipped with General Electric CF6–45 or –50 series engines. 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. Modification (f) Within 24 months after the effective date of this AD: Modify the side cowl assemblies on the engines by replacing existing wear plates with new extended wear plates and installing new stop fittings, by doing all actions according to the Accomplishment Instructions of Boeing E:\FR\FM\21MRR1.SGM 21MRR1 Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations Service Bulletin 747–71–2300, Revision 1, dated October 30, 2003. Any applicable corrective actions must be done before further flight. DEPARTMENT OF TRANSPORTATION On Condition: Removal of Bulb Seals and Other Specified Actions 14 CFR Part 39 (g) If bulb seals were installed on the trailing edge of the fan thrust reverser in accordance with Boeing Service Letter 747– SL–71–045: Concurrently with or before further flight after accomplishing paragraph (f) of this AD, remove the bulb seals, plug the open holes in the trailing edge of the fan thrust reverser, and adjust the cowl latches as applicable, in accordance with Boeing Service Letter 747–SL–71–045–C, dated April 10, 2003. Alternative Methods of Compliance (AMOCs) (h) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) You must use Boeing Service Bulletin 747–71–2300, Revision 1, dated October 30, 2003; and Boeing Service Letter 747–SL–71– 045–C, including Attachment, dated April 10, 2003; as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of those documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741–6030, or go to: https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Nassif Building, Washington, DC. Issued in Renton, Washington, on March 8, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–5298 Filed 3–18–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 15:51 Mar 18, 2005 Jkt 205001 Federal Aviation Administration [Docket No. FAA–2004–19535; Directorate Identifier 2004–NM–78–AD; Amendment 39– 14020; AD 2005–06–12] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SP, and 747SR Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SP, and 747SR series airplanes. That AD currently requires one-time inspections for cracking in certain upper deck floor beams and follow-on actions. This new AD expands the existing inspection area and requires inspecting fastener holes in certain areas of airplanes modified previously, and taking corrective actions if necessary. This action also defines new sources for instructions for repairs and post-modification/repair inspections. This AD is prompted by reports of fatigue cracking of the upper chord of certain upper deck floor beams. We are issuing this AD to find and fix cracking in certain upper deck floor beams, which could extend and sever floor beams adjacent to the body frame and result in rapid depressurization and loss of controllability of the airplane. DATES: This AD becomes effective April 25, 2005. The incorporation by reference of Boeing Service Bulletin 747–53A2459, Revision 1, dated March 11, 2004, is approved by the Director of the Federal Register as of April 25, 2005. On October 16, 2002 (67 FR 57510, September 11, 2002), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747–53A2459, dated January 11, 2001. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 13349 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2004–19535; the directorate identifier for this docket is 2004–NM– 78–AD. FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6437; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the Federal Aviation Regulations (14 CFR Part 39) with an AD to supersede AD 2002–18–04, amendment 39–12878 (67 FR 57510, September 11, 2002). The existing AD applies to certain Boeing Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–300, 747SP, and 747SR series airplanes. The proposed AD was published in the Federal Register on November 5, 2004 (69 FR 64525), to continue to require one-time inspections for cracking in certain upper deck floor beams and follow-on actions. The proposed AD would expand the existing inspection area, and would require inspecting fastener holes in certain areas of airplanes modified previously, and taking corrective actions if necessary. The proposed AD also would define new sources for instructions for repairs and postmodification/repair inspections. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD by a single commenter. Request To Revise Delegation Language The commenter requests that we revise the proposed AD to change references to approval of repairs or alternative methods of compliance (AMOCs) by Boeing Company Designated Engineering Representatives (DERs). The commenter states that these provisions should refer to approval by Authorized Representatives (ARs) of the Boeing Delegation Option Authorization (DOA) Organization. The commenter notes that, since the issuance of the proposed AD, Boeing has received a DOA. We concur. We have revised paragraphs (h)(1)(i), (h)(2), and (i) of this E:\FR\FM\21MRR1.SGM 21MRR1

Agencies

[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13347-13349]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5298]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19945; Directorate Identifier 2004-NM-22-AD;
Amendment 39-14017; AD 2005-06-09]
RIN 2120-AA64

Airworthiness Directives; Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, and 747SR Series Airplanes Equipped With General
Electric (GE) CF6-45 or -50 Series Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747-200B, 747-200C, 747-200F, 747-300, and 747SR
series airplanes, equipped with GE CF6-45 or -50 series engines. This
AD requires modifying the side cowl assemblies on the engines by
replacing existing wear plates with new extended wear plates and
installing new stop fittings. This AD is prompted by reports of a gap
at the interface of the lower portion of the side cowl and the aft
flange of the thrust reverser. We are issuing this AD to prevent an
excessive quantity of air from entering the fire zone that surrounds
the engine, which, in the event of an engine fire, could result in an
inability to control or extinguish the fire.

DATES: This AD becomes effective April 25, 2005.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of April
25, 2005.

ADDRESSES: For service information identified in this AD, contact
Boeing

[[Page 13348]]

Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207.
Docket: The AD docket contains the proposed AD, comments, and any
final disposition. You can examine the AD docket on the Internet at
https://dms.dot.gov, or in person at the Docket Management Facility
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the U.S.
Department of Transportation, 400 Seventh Street, SW., room PL-401,
Washington, DC. This docket number is FAA-2004-19945; the directorate
identifier for this docket is 2004-NM-22-AD.

FOR FURTHER INFORMATION CONTACT: Dan Kinney, Aerospace Engineer,
Propulsion Branch, ANM-140S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone
(425) 917-6499; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with an AD for certain Boeing Model 747-200B, 747-200C, 747-200F, 747-
300, and 747SR series airplanes, equipped with General Electric CF6-45
or -50 series engines. That action, published in the Federal Register
on January 3, 2005 (70 FR 51), proposed to require modifying the side
cowl assemblies on the engines by replacing existing wear plates with
new extended wear plates and installing new stop fittings.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment that has
been submitted on the proposed AD. The commenter supports the proposed
AD.

Conclusion

We have carefully reviewed the available data, including the
comment that has been submitted, and determined that air safety and the
public interest require adopting the AD as proposed.

Costs of Compliance

There are about 140 airplanes of the affected design in the
worldwide fleet. This AD affects about 38 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD.

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Average
Action Work hours labor rate Parts Cost per Fleet cost
per hour airplane
----------------------------------------------------------------------------------------------------------------
Modification per Boeing Service Bulletin 747- 72 $65 $25,736 $30,416 $1,155,808
71-2300, Revision 1..........................
----------------------------------------------------------------------------------------------------------------

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 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, 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 airworthiness
directive (AD):

2005-06-09 Boeing: Amendment 39-14017. Docket No. FAA-2004-19945;
Directorate Identifier 2004-NM-22-AD.

Effective Date

(a) This AD becomes effective April 25, 2005.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Boeing Model 747-200B, 747-200C, 747-
200F, 747-300, and 747SR series airplanes; certificated in any
category; equipped with General Electric CF6-45 or -50 series
engines.

Unsafe Condition

(d) This AD was prompted by reports of a gap at the interface of
the lower portion of the side cowl and the aft flange of the thrust
reverser. We are issuing this AD to prevent an excessive quantity of
air from entering the fire zone that surrounds the engine, which, in
the event of an engine fire, could result in an inability to control
or extinguish the fire.

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.

Modification

(f) Within 24 months after the effective date of this AD: Modify
the side cowl assemblies on the engines by replacing existing wear
plates with new extended wear plates and installing new stop
fittings, by doing all actions according to the Accomplishment
Instructions of Boeing

[[Page 13349]]

Service Bulletin 747-71-2300, Revision 1, dated October 30, 2003.
Any applicable corrective actions must be done before further
flight.

On Condition: Removal of Bulb Seals and Other Specified Actions

(g) If bulb seals were installed on the trailing edge of the fan
thrust reverser in accordance with Boeing Service Letter 747-SL-71-
045: Concurrently with or before further flight after accomplishing
paragraph (f) of this AD, remove the bulb seals, plug the open holes
in the trailing edge of the fan thrust reverser, and adjust the cowl
latches as applicable, in accordance with Boeing Service Letter 747-
SL-71-045-C, dated April 10, 2003.

Alternative Methods of Compliance (AMOCs)

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

Material Incorporated by Reference

(i) You must use Boeing Service Bulletin 747-71-2300, Revision
1, dated October 30, 2003; and Boeing Service Letter 747-SL-71-045-
C, including Attachment, dated April 10, 2003; as applicable, to
perform the actions that are required by this AD, unless the AD
specifies otherwise. The Director of the Federal Register approves
the incorporation by reference of those documents in accordance with
5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service
information, contact Boeing Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124-2207. For information on the availability
of this material at the National Archives and Records Administration
(NARA), call (202) 741-6030, or go to: https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html. You may view the AD docket at the Docket Management
Facility, U.S. Department of Transportation, 400 Seventh Street,
SW., room PL-401, Nassif Building, Washington, DC.

Issued in Renton, Washington, on March 8, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-5298 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P

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