Airworthiness Directives; Boeing Model 747-200B, -200C, -200F, and -400F Series Airplanes, 20273-20275 [05-7683]

Download as PDF Federal Register / Vol. 70, No. 74 / Tuesday, April 19, 2005 / Rules and Regulations When Does This AD Become Effective? PART 39—AIRWORTHINESS DIRECTIVES (a) This AD becomes effective on June 2, 2005. 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] What Other ADs Are Affected by This Action? (b) None. What Gliders Are Affected by This AD? 2. FAA amends § 39.13 by adding a new AD to read as follows: I 2005–08–06 Centrair: Amendment 39– 14058; Docket No. FAA–2004–19616; Directorate Identifier 2004–CE–38–AD. (c) This AD affects Models 101, 101A, 101AP, and 101P gliders, all serial numbers, without elevator and aileron part number SY991A hinge pins installed, certificated in any category. 20273 What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control. (e) To address this problem, you must do the following: Actions Compliance Procedures (1) Replace any installed elevator and aileron hinge pins that are not part number (P/N) SY991A hinge pins with P/N SY991A hinge pins. (2) Do not install any elevator and aileron hinge pins that are not P/N SY991A hinge pins as specified in paragraph (e)(1) of this AD. Within the next 25 hours time-in-service (TIS) after June 2, 2005 (the effective date of this AD), unless already done. ´ ´ Follow Societe Nouvelle Centrair Service Bulletin No. 101–22, dated March 13, 2001. As of June 2, 2005 (the effective date of this AD). Not Applicable. May I Request an Alternative Method of Compliance? dms.dot.gov. The docket number is FAA– 2004–19616. (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; facsimile: (816) 329–4090. Issued in Kansas City, Missouri, on April 11, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7564 Filed 4–18–05; 8:45 am] Is There Other Information That Relates to This Subject? (g) French AD Number 2001–247(A), dated June 27, 2001, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by ´ ´ this AD following the instructions in Societe Nouvelle Centrair Service Bulletin No. 101– 22, dated March 13, 2001. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact CENTRAIR, Aerodome B.P.N. 44, 36300 Le Blanc, France; telephone: 02.54.37.07.96; facsimile: 02.54.37.48.64. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at https:// VerDate jul<14>2003 14:37 Apr 18, 2005 Jkt 205001 BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–20136; Directorate Identifier 2004–NM–185–AD; Amendment 39–14061; AD 2005–08–09] RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–200B, –200C, –200F, and –400F Series Airplanes 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 series airplanes. This AD requires repetitive detailed inspections for cracks in the crease beam and adjacent structure of the fuselage, and related investigative and corrective actions if necessary. This AD is prompted by fatigue cracks found in the crease beam during a follow-on inspection of a previously installed modification. We are issuing this AD to find and fix fatigue cracking of the fuselage frame, which could result in PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 reduced structural integrity of the frame and consequent rapid decompression of the airplane. DATES: This AD becomes effective May 24, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of May 24, 2005. ADDRESSES: The service information referenced in this AD may be obtained from 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 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–2005–20136; the directorate identifier for this docket is 2005–NM– 185–AD. FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6432; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with an AD for certain Boeing Model 747 series airplanes. That action, published in the Federal Register on January 28, E:\FR\FM\19APR1.SGM 19APR1 20274 Federal Register / Vol. 70, No. 74 / Tuesday, April 19, 2005 / Rules and Regulations 2005 (70 FR 4048), proposed to require repetitive detailed inspections for cracks in the crease beam and adjacent structure of the fuselage, and related investigative and corrective actions if necessary. 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 163 airplanes of the affected design in the worldwide fleet. This AD will affect about 30 airplanes of U.S. registry. The inspection will take about 8 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the inspection for U.S. operators is $15,600, or $520 per airplane, per inspection cycle. 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 VerDate jul<14>2003 14:37 Apr 18, 2005 Jkt 205001 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. 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. Repetitive Inspections Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. (f) Accomplish a detailed inspection for cracks in the crease beam and adjacent structure of the fuselage by doing all the applicable actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2504, dated August 19, 2004; at the applicable time specified in paragraph (f)(1) or (f)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 6,000 flight cycles. (1) For Groups 1 and 2 airplanes as identified in the service bulletin: Before the accumulation of 10,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later. (2) For Groups 3 and 4 airplanes as identified in the service bulletin: Before the accumulation of 14,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later. Adoption of the Amendment Related Investigative and Corrective Actions Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (g) If any crack is found during any inspection required by paragraph (f) of this AD: Before further flight, repair the cracking in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2504, dated August 19, 2004. If cracking of the crease beam or outer tee chord attachment is found: Before further flight, do a high frequency eddy current inspection for additional cracking, and repair any cracking found, in accordance with the service bulletin. Where the service bulletin specifies contacting the manufacturer for disposition of certain repair conditions, repair before further flight in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or by an Authorized Representative for the Boeing Delegation Option Authorization (DOA) 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, and the approval must specifically refer to this AD. List of Subjects in 14 CFR Part 39 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 2005–08–09 Boeing: Amendment 39–14061. Docket No. FAA–2005–20136; Directorate Identifier 2004–NM–185–AD. Effective Date (a) This AD becomes effective May 24, 2005. No Reporting Required Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 200B, –200C, –200F, and –400F series airplanes, line numbers 604 and subsequent, certificated in any category; as listed in Boeing Alert Service Bulletin 747–53A2504, dated August 19, 2004. Unsafe Condition (d) This AD was prompted by fatigue cracks found in the crease beam during a follow-on inspection of a previously installed modification. We are issuing this AD to find and fix fatigue cracking of the fuselage frame, which could result in reduced structural integrity of the frame and consequent rapid decompression of the airplane. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 (h) For certain airplanes, the service bulletin referenced in this AD recommends reporting any discrepancies to the manufacturer, but this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for a repair required by this AD, if it is approved by an Authorized Representative for the Boeing DOA Organization who has been authorized by the Manager, Seattle ACO, to make such findings. E:\FR\FM\19APR1.SGM 19APR1 Federal Register / Vol. 70, No. 74 / Tuesday, April 19, 2005 / Rules and Regulations Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 747–53A2504, dated August 19, 2004, 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 this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, go to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 11, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–7683 Filed 4–18–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19810; Directorate Identifier 2004–NM–119–AD; Amendment 39–14062; AD 2005–08–10] RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–600, –700, and –800 Series Airplanes 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 737–600, –700, and –800 series airplanes. This AD requires doing a general visual inspection for sealant at the interface of the upper spar fittings, strut side skins, and the fittings of the thrust reverser strut fairing on the engine struts; and applying an injection seal or silicone sponge rubber with fillet seal if necessary. This AD is prompted by a report that an injection seal in the engine strut area may not have been properly completed or installed during production. We are issuing this AD to prevent flammable fluid (such as fuel or hydraulic fluid) from leaking onto a hot engine exhaust nozzle or into the engine VerDate jul<14>2003 14:37 Apr 18, 2005 Jkt 205001 core fire zone, and consequently causing an uncontrolled fire or explosion. DATES: This AD becomes effective May 24, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of May 24, 2005. 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 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–2004–19810; the directorate identifier for this docket is 2004–NM– 119–AD. FOR FURTHER INFORMATION CONTACT: Doug Pegors, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6504; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with an AD for certain Boeing Model 737– 600, –700, and –800 series airplanes. That action, published in the Federal Register on December 14, 2004 (69 FR 74465), proposed to require doing a general visual inspection for sealant at the interface of the upper spar fittings, strut side skins, and the fittings of the thrust reverser strut fairing on the engine struts; and applying an injection seal or silicone sponge rubber with fillet seal if necessary. 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. Three commenters support the proposed AD. Request for Shortening the Compliance Time A commenter supports the proposed AD, but requests that the compliance time of 18 months or 3,500 flight cycles be shortened. The commenter suggests that, due to the low cost of modifying an airplane, short repair time, and the PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 20275 potential severity of a failure, the compliance time is too long. We do not agree with the commenter’s suggestion. In developing an appropriate compliance time, we considered the safety implications and normal maintenance schedules for timely accomplishment of the required inspection and repair. Further, we arrived at the compliance time with operator and manufacturer concurrence. In consideration of all of these factors, we determined that the compliance time, represents an appropriate interval in which the engine nacelle struts can be inspected, and repaired if required, in a timely manner within the fleet, while still maintaining an adequate level of safety. Operators are always permitted to accomplish the requirements of an AD at a time earlier than the specified compliance time. If additional data are presented that would justify a shorter compliance time, we may consider further rulemaking on this issue. Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 257 airplanes worldwide of the affected design. This AD will affect about 99 airplanes of U.S. registry. The inspection will take about 2 work hours per airplane, at an average labor rate of $65 per work hour. Based on these figures, the estimated cost of the AD for U.S. operators is $12,870, or $130 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 E:\FR\FM\19APR1.SGM 19APR1

Agencies

[Federal Register Volume 70, Number 74 (Tuesday, April 19, 2005)]
[Rules and Regulations]
[Pages 20273-20275]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7683]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20136; Directorate Identifier 2004-NM-185-AD; 
Amendment 39-14061; AD 2005-08-09]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200B, -200C, -200F, 
and -400F Series Airplanes

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 series airplanes. This AD requires repetitive 
detailed inspections for cracks in the crease beam and adjacent 
structure of the fuselage, and related investigative and corrective 
actions if necessary. This AD is prompted by fatigue cracks found in 
the crease beam during a follow-on inspection of a previously installed 
modification. We are issuing this AD to find and fix fatigue cracking 
of the fuselage frame, which could result in reduced structural 
integrity of the frame and consequent rapid decompression of the 
airplane.

DATES: This AD becomes effective May 24, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of May 
24, 2005.

ADDRESSES: The service information referenced in this AD may be 
obtained from 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 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-2005-20136; the directorate 
identifier for this docket is 2005-NM-185-AD.

FOR FURTHER INFORMATION CONTACT: Nick Kusz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6432; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with an AD for certain Boeing Model 747 series airplanes. That action, 
published in the Federal Register on January 28,

[[Page 20274]]

2005 (70 FR 4048), proposed to require repetitive detailed inspections 
for cracks in the crease beam and adjacent structure of the fuselage, 
and related investigative and corrective actions if necessary.

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 163 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 30 airplanes of U.S. 
registry. The inspection will take about 8 work hours per airplane, at 
an average labor rate of $65 per work hour. Based on these figures, the 
estimated cost of the inspection for U.S. operators is $15,600, or $520 
per airplane, per inspection cycle.

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):

2005-08-09 Boeing: Amendment 39-14061. Docket No. FAA-2005-20136; 
Directorate Identifier 2004-NM-185-AD.

Effective Date

    (a) This AD becomes effective May 24, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-200B, -200C, -200F, and 
-400F series airplanes, line numbers 604 and subsequent, 
certificated in any category; as listed in Boeing Alert Service 
Bulletin 747-53A2504, dated August 19, 2004.

Unsafe Condition

    (d) This AD was prompted by fatigue cracks found in the crease 
beam during a follow-on inspection of a previously installed 
modification. We are issuing this AD to find and fix fatigue 
cracking of the fuselage frame, which could result in reduced 
structural integrity of the frame and consequent rapid decompression 
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.

Repetitive Inspections

    (f) Accomplish a detailed inspection for cracks in the crease 
beam and adjacent structure of the fuselage by doing all the 
applicable actions in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 747-53A2504, dated 
August 19, 2004; at the applicable time specified in paragraph 
(f)(1) or (f)(2) of this AD. Repeat the inspection thereafter at 
intervals not to exceed 6,000 flight cycles.
    (1) For Groups 1 and 2 airplanes as identified in the service 
bulletin: Before the accumulation of 10,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever is later.
    (2) For Groups 3 and 4 airplanes as identified in the service 
bulletin: Before the accumulation of 14,000 total flight cycles, or 
within 1,500 flight cycles after the effective date of this AD, 
whichever is later.

Related Investigative and Corrective Actions

    (g) If any crack is found during any inspection required by 
paragraph (f) of this AD: Before further flight, repair the cracking 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 747-53A2504, dated August 19, 2004. If cracking of 
the crease beam or outer tee chord attachment is found: Before 
further flight, do a high frequency eddy current inspection for 
additional cracking, and repair any cracking found, in accordance 
with the service bulletin. Where the service bulletin specifies 
contacting the manufacturer for disposition of certain repair 
conditions, repair before further flight in accordance with a method 
approved by the Manager, Seattle Aircraft Certification Office 
(ACO), FAA; or by an Authorized Representative for the Boeing 
Delegation Option Authorization (DOA) 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, and the approval must 
specifically refer to this AD.

No Reporting Required

    (h) For certain airplanes, the service bulletin referenced in 
this AD recommends reporting any discrepancies to the manufacturer, 
but this AD does not include that requirement.

Alternative Methods of Compliance (AMOCs)

    (i)(1) The Manager, Seattle ACO, has the authority to approve 
AMOCs for this AD, if requested in accordance with the procedures 
found in 14 CFR 39.19.
    (2) An AMOC that provides an acceptable level of safety may be 
used for a repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing DOA Organization who has 
been authorized by the Manager, Seattle ACO, to make such findings.

[[Page 20275]]

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 747-53A2504, 
dated August 19, 2004, 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 this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To 
get copies of the service information, go to Boeing Commercial 
Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view 
the AD docket, go to the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street SW., room PL-401, Nassif 
Building, Washington, DC. To review copies of the service 
information, go to the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_
locations.html.

    Issued in Renton, Washington, on April 11, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7683 Filed 4-18-05; 8:45 am]
BILLING CODE 4910-13-P
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