Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300 Series Airplanes; and Model 747SP and 747SR Series Airplanes; Equipped With Pratt and Whitney Model JT9D-3 or -7 (Except -70) Series Engines, 12115-12117 [05-4411]

Download as PDF Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations and consequent rapid decompression of the airplane fuselage. 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. One-Time Inspection/Investigative and Corrective Actions (f) Before the accumulation of 4,000 total flight cycles, or within 1,000 flight cycles after the effective date of this AD, whichever is later: Perform a detailed inspection for discrepancies of the fuselage frame to tension tie joints at BS 1120 through BS 1220, and to determine if steel splice plates are installed on the fuselage frames. Do the inspection in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53– 2483, Revision 1, dated August 28, 2003. Do any applicable investigative and corrective actions before further flight in accordance with the service bulletin, except as provided by paragraph (h) of this AD. Note 1: For the purposes of this AD, a detailed inspection is: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ Determining Number of Flight Cycles for Compliance Time (g) For the purposes of calculating the compliance threshold for the actions required by paragraph (f) of this AD, all pressurized flight cycles, including the number of flight cycles in which cabin differential pressure is at 2.0 pounds per square inch (psi) or less, must be counted when determining the number of flight cycles that have occurred on the airplane. Where the service bulletin and this AD differ, the AD prevails. Repair Requirements (h) For any repairs outside the limits of Boeing Special Attention Service Bulletin 747–53–2483, Revision 1, dated August 28, 2003, or if any aluminum splice plate is installed on the fuselage frames: Before further flight, repair or replace, as applicable, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or in accordance with data meeting the certification basis of the airplane approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair or replacement method to be approved, as required by this paragraph, the approval must specifically refer to this AD. AD in accordance with Boeing Special Attention Service Bulletin 747–53–2483, dated October 24, 2002, are considered acceptable for compliance with the corresponding actions specified in this AD. DEPARTMENT OF TRANSPORTATION No Reporting Requirements [Docket No. FAA–2004–19812; Directorate Identifier 2003–NM–197–AD; Amendment 39–13996; AD 2005–05–07] (j) Although the Accomplishment Instructions of Boeing Special Attention Service Bulletin 747–53–2483, Revision 1, dated August 28, 2003; describe procedures for submitting certain information to the manufacturer, this AD does not require that action. Alternative Methods of Compliance (AMOCs) (k)(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 any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Material Incorporated by Reference (l) You must use Boeing Special Attention Service Bulletin 747–53–2483, Revision 1, dated August 28, 2003, 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. 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 February 28, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–4410 Filed 3–10–05; 8:45 am] BILLING CODE 4910–13–P Actions Accomplished Per Previous Issue of Service Bulletin (i) Inspections and corrective actions accomplished before the effective date of this VerDate jul<14>2003 17:11 Mar 10, 2005 Jkt 205001 12115 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; Boeing Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, and –300 Series Airplanes; and Model 747SP and 747SR Series Airplanes; Equipped With Pratt and Whitney Model JT9D–3 or –7 (Except –70) 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 transport category airplanes. This AD requires repetitive detailed inspections to detect cracking of the aft and forward surfaces of the bulkhead web at nacelle station 180, and repair if necessary. This AD is prompted by reports of cracking of the web bulkhead at nacelle station 180. We are issuing this AD to detect and correct fatigue cracking of the web bulkhead, and consequent loss of the load path of the bulkhead at nacelle station 180, which when combined with the loss of the midspar load path, could result in the in-flight separation of the engine and strut. Such separation may result in secondary damage to the airplane and consequent reduced controllability of the airplane. DATES: This AD becomes effective April 15, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of April 15, 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 E:\FR\FM\11MRR1.SGM 11MRR1 12116 Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations FAA–2004–19812; the directorate identifier for this docket is 2003–NM– 197–AD. FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6421; fax (425) 917–6590. The FAA proposed to amend 14 CFR Part 39 with an AD for certain Boeing Model 747– 100, –100B, –100B SUD, –200B, –200C, –200F, and –300 series airplanes; and Model 747SP and 747SR series airplanes; equipped with Pratt and Whitney Model JT9D–3 or –7 (except –70) series engines. That action, published in the Federal Register on December 8, 2004 (69 FR 70936), proposed to require repetitive detailed inspections to detect cracking of the aft and forward surfaces of the bulkhead web at nacelle station 180, and repair if necessary. SUPPLEMENTARY INFORMATION: Comments We provided the public the opportunity to participate in the development of this AD. No comments have been submitted on the proposed AD or on the determination of the cost to the public. Explanation of Change to Proposed AD Boeing has received a Delegation Option Authorization (DOA). We have revised this final rule to delegate the authority to approve an alternative method of compliance for any repair required by this AD to the Authorized Representative for the Boeing DOA Organization rather than the Designated Engineering Representative. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD with the change described previously. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD. This AD will affect about 223 airplanes worldwide and 73 airplanes of U.S. registry. The required actions will take about 1 work hour 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 $4,745, or $65 per airplane, per inspection cycle. 17:11 Mar 10, 2005 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 Costs of Compliance VerDate jul<14>2003 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. Jkt 205001 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 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 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 2005–05–07 Boeing: Amendment 39–13996. Docket No. FAA–2004–19812; Directorate Identifier 2003–NM–197–AD. Effective Date (a) This AD becomes effective April 15, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Boeing Model 747– 100, –100B, –100B SUD, –200B, –200C, –200F, and –300 series airplanes; and Model 747SP and 747SR series airplanes; equipped with Pratt and Whitney Model JT9D–3, or –7 (except for –70) series engines; as identified in Boeing Alert Service Bulletin 747– 54A2220, dated July 31, 2003; certificated in any category. Unsafe Condition (d) This AD was prompted by reports of cracking of the web bulkhead at nacelle station 180. We are issuing this AD to detect and correct fatigue cracking of the web bulkhead, and consequent loss of the load path of the bulkhead at nacelle station 180, which when combined with the loss of the midspar load path, could result in the inflight separation of the engine and strut. Such separation may result in secondary damage to the airplane 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. Repetitive Inspections and Repair (f) Within 9 months after the effective date of this AD, do a detailed inspection to detect cracking of the aft and forward surfaces of the bulkhead web at nacelle station 180, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2220, dated July 31, 2003. (1) If no cracking is detected, repeat the detailed inspection at the applicable intervals specified in the ‘‘Repeat Inspection Interval’’ column of Tables 1 and 2 in Figure 1 of the service bulletin. (2) If any cracking is detected, before further flight, repair the cracking in accordance with the service bulletin, except as provided by paragraph (f)(3) of this AD. Thereafter, repeat the detailed inspection at the applicable intervals specified in the ‘‘Repeat Inspection Interval’’ column of Tables 1 and 2 in Figure 1 of the service bulletin. (3) If any cracking exceeds the repair limits specified in the applicable structural repair manual (referenced in the service bulletin), before further flight, repair the cracking in accordance with a method approved by the Manager, Seattle Aircraft Certification Office E:\FR\FM\11MRR1.SGM 11MRR1 Federal Register / Vol. 70, No. 47 / Friday, March 11, 2005 / Rules and Regulations (ACO), FAA; or in accordance with data meeting the certification basis of the airplane approved by an Authorized Representative (AR) 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. DEPARTMENT OF TRANSPORTATION Alternative Methods of Compliance (AMOCs) Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–600); and Model A310 Series Airplanes; Equipped With Certain Honeywell Inertial Reference Units (IRU) (g)(1) The Manager, Seattle ACO, FAA, 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 any repair required by this AD, if it is approved by an AR for the Boeing 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. Material Incorporated by Reference (h) You must use Boeing Alert Service Bulletin 747–54A2220, dated July 31, 2003, 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. 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 February 28, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–4411 Filed 3–10–05; 8:45 am] BILLING CODE 4910–13–P VerDate jul<14>2003 17:11 Mar 10, 2005 Jkt 205001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–19537; Directorate Identifier 2004–NM–145–AD; Amendment 39–13993; AD 2005–05–05] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300–600); and Model A310 series airplanes; equipped with certain Honeywell inertial reference units (IRUs). This AD requires revising the Limitations section of the airplane flight manual to prohibit the use of CAT 2 and CAT 3 automatic landing and rollout procedures at certain airports. This AD is prompted by a report that some magnetic deviation tables in the IRU database are obsolete and contain significant differences with the real magnetic deviations. We are issuing this AD to prevent an airplane from deviating from the runway centerline, and possibly departing the runway. This AD becomes effective April 15, 2005. The incorporation by reference of certain publications listed in the AD is approved by the Director of the Federal Register as of April 15, 2005. ADDRESSES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. 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, DATES: PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 12117 400 Seventh Street, SW., room PL–401, Washington, DC. This docket number is FAA–2004–19537; the directorate identifier for this docket is 2004–NM– 145–AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with an AD for all Airbus Model A300 B4– 600, B4–600R, and F4–600R series airplanes, and Model C4–605R Variant F airplanes (collectively called A300– 600); and Model A310 series airplanes; equipped with certain Honeywell inertial reference units (IRUs). That action, published in the Federal Register on November 5, 2004 (69 FR 64520), proposed to require revising the Limitations section of the airplane flight manual (AFM) to prohibit the use of CAT 2 and CAT 3 automatic landing and rollout procedures at certain airports. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment that has been submitted on the proposed AD. The commenter supports the proposed AD. Explanation of Changes Made to This Final Rule We have revised Table 2 of this AD to more clearly identify the applicable airplane flight manuals (AFM) to be revised. In Table 2 of the proposed AD we referenced an incorrect date for the temporary revisions. We have revised Table 2 of this final rule to correct that information. 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, with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance This AD will affect about 136 airplanes of U.S. registry. The AFM revision will take about 1 work hour per airplane, at an average labor rate of $65 per work hour. Based on these figures, E:\FR\FM\11MRR1.SGM 11MRR1

Agencies

[Federal Register Volume 70, Number 47 (Friday, March 11, 2005)]
[Rules and Regulations]
[Pages 12115-12117]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-4411]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19812; Directorate Identifier 2003-NM-197-AD; 
Amendment 39-13996; AD 2005-05-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD, 
-200B, -200C, -200F, and -300 Series Airplanes; and Model 747SP and 
747SR Series Airplanes; Equipped With Pratt and Whitney Model JT9D-3 or 
-7 (Except -70) 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 transport category airplanes. This AD requires 
repetitive detailed inspections to detect cracking of the aft and 
forward surfaces of the bulkhead web at nacelle station 180, and repair 
if necessary. This AD is prompted by reports of cracking of the web 
bulkhead at nacelle station 180. We are issuing this AD to detect and 
correct fatigue cracking of the web bulkhead, and consequent loss of 
the load path of the bulkhead at nacelle station 180, which when 
combined with the loss of the midspar load path, could result in the 
in-flight separation of the engine and strut. Such separation may 
result in secondary damage to the airplane and consequent reduced 
controllability of the airplane.

DATES: This AD becomes effective April 15, 2005.
    The incorporation by reference of certain publications listed in 
the AD is approved by the Director of the Federal Register as of April 
15, 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

[[Page 12116]]

FAA-2004-19812; the directorate identifier for this docket is 2003-NM-
197-AD.

FOR FURTHER INFORMATION CONTACT: Tamara Anderson, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6421; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 
with an AD for certain Boeing Model 747-100, -100B, -100B SUD, -200B, -
200C, -200F, and -300 series airplanes; and Model 747SP and 747SR 
series airplanes; equipped with Pratt and Whitney Model JT9D-3 or -7 
(except -70) series engines. That action, published in the Federal 
Register on December 8, 2004 (69 FR 70936), proposed to require 
repetitive detailed inspections to detect cracking of the aft and 
forward surfaces of the bulkhead web at nacelle station 180, and repair 
if necessary.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. No comments have been submitted on the proposed 
AD or on the determination of the cost to the public.

Explanation of Change to Proposed AD

    Boeing has received a Delegation Option Authorization (DOA). We 
have revised this final rule to delegate the authority to approve an 
alternative method of compliance for any repair required by this AD to 
the Authorized Representative for the Boeing DOA Organization rather 
than the Designated Engineering Representative.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously. We have determined that this change will 
neither increase the economic burden on any operator nor increase the 
scope of the AD.

Costs of Compliance

    This AD will affect about 223 airplanes worldwide and 73 airplanes 
of U.S. registry. The required actions will take about 1 work hour 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 $4,745, or 
$65 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

    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):

2005-05-07 Boeing: Amendment 39-13996. Docket No. FAA-2004-19812; 
Directorate Identifier 2003-NM-197-AD.

Effective Date

    (a) This AD becomes effective April 15, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 747-100, -100B, -100B SUD, -
200B, -200C, -200F, and -300 series airplanes; and Model 747SP and 
747SR series airplanes; equipped with Pratt and Whitney Model JT9D-
3, or -7 (except for -70) series engines; as identified in Boeing 
Alert Service Bulletin 747-54A2220, dated July 31, 2003; 
certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports of cracking of the web 
bulkhead at nacelle station 180. We are issuing this AD to detect 
and correct fatigue cracking of the web bulkhead, and consequent 
loss of the load path of the bulkhead at nacelle station 180, which 
when combined with the loss of the midspar load path, could result 
in the in-flight separation of the engine and strut. Such separation 
may result in secondary damage to the airplane 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.

Repetitive Inspections and Repair

    (f) Within 9 months after the effective date of this AD, do a 
detailed inspection to detect cracking of the aft and forward 
surfaces of the bulkhead web at nacelle station 180, in accordance 
with the Accomplishment Instructions of Boeing Alert Service 
Bulletin 747-54A2220, dated July 31, 2003.
    (1) If no cracking is detected, repeat the detailed inspection 
at the applicable intervals specified in the ``Repeat Inspection 
Interval'' column of Tables 1 and 2 in Figure 1 of the service 
bulletin.
    (2) If any cracking is detected, before further flight, repair 
the cracking in accordance with the service bulletin, except as 
provided by paragraph (f)(3) of this AD. Thereafter, repeat the 
detailed inspection at the applicable intervals specified in the 
``Repeat Inspection Interval'' column of Tables 1 and 2 in Figure 1 
of the service bulletin.
    (3) If any cracking exceeds the repair limits specified in the 
applicable structural repair manual (referenced in the service 
bulletin), before further flight, repair the cracking in accordance 
with a method approved by the Manager, Seattle Aircraft 
Certification Office

[[Page 12117]]

(ACO), FAA; or in accordance with data meeting the certification 
basis of the airplane approved by an Authorized Representative (AR) 
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.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Seattle ACO, FAA, 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 any repair required by this AD, if it is approved by an AR 
for the Boeing 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.

Material Incorporated by Reference

    (h) You must use Boeing Alert Service Bulletin 747-54A2220, 
dated July 31, 2003, 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. 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 February 28, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-4411 Filed 3-10-05; 8:45 am]
BILLING CODE 4910-13-P

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