[Federal Register Volume 70, Number 3 (Wednesday, January 5, 2005)]
[Rules and Regulations]
[Pages 679-680]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-105]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19200; Directorate Identifier 2003-NM-195-AD; 
Amendment 39-13927; AD 2005-01-03]
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 & Whitney JT9D-3 and -7 
(Except -70) Series Engines or General Electric CF6-50 Series Engines 
With Modified JT9D-7 Inboard Struts

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing airplanes listed above. This AD requires repetitive 
detailed inspections of the midspar web of the inboard and/or outboard 
struts for cracking, disbonding, or buckling; repetitive detailed 
inspections of the midspar stiffeners for any crack or fracture; 
related investigative actions; and corrective actions, if necessary. 
This AD is prompted by reports of cracking in the midspar web. We are 
issuing this AD to detect and correct cracking in the midspar assembly, 
which could result in the loss of the midspar assembly load path, and 
could, combined with the loss of the nacelle station 180 bulkhead load 
path, lead to the separation of the engine from the airplane.

DATES: This AD becomes effective February 9, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of 
February 9, 2005.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207. You can examine this information at the National Archives and 
Records Administration (NARA). For information on the availability of 
this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    You can examine the contents of this AD docket on the Internet at 
http://dms.dot.gov, or in person at the Docket Management Facility, 
U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, 
on the plaza level of the Nassif Building, Washington, DC. This docket 
number is FAA-2004-19200; the directorate identifier for this docket is 
2003-NM-195-AD.

FOR FURTHER INFORMATION CONTACT: Candice Gerretsen, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6428; fax (425) 917-6590.

Examining the Docket

    The AD docket contains the proposed AD, comments, and any final 
disposition. You can examine the AD docket on the Internet at http://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 DOT 
street address stated in the ADDRESSES section.

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 & Whitney JT9D-3 and -7 (except -
70) series engines or General Electric CF6-50 series engines with 
modified JT9D-7 inboard struts. That action, published in the Federal 
Register on September 29, 2004 (69 FR 58101), proposed to require 
repetitive detailed inspections of the midspar web of the inboard and/
or outboard struts for cracking, disbonding, or buckling; repetitive 
detailed inspections of the midspar stiffeners for any crack or 
fracture; related investigative actions; and corrective actions, if 
necessary.

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, the manufacturer, 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 228 airplanes of the affected design worldwide and 
78 airplanes of U.S. registry. The actions will take about 6 to 13 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 between $30,420 and $65,910, or between $390 and $845 per airplane, 
per inspection cycle.

Authority for This Rulemaking

    The FAA's authority to issue rules regarding aviation safety is 
found in Title 49 of the United States Code. 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.
    This rulemaking is promulgated under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, the FAA is charged with promoting 
safety 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 AD.

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 the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act. We prepared a regulatory evaluation 
of the estimated costs to comply with this AD. See the

[[Page 680]]

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):

2005-01-03 Boeing: Amendment 39-13927. Docket No. FAA-2004-19200; 
Directorate Identifier 2003-NM-195-AD.

Effective Date

    (a) This AD becomes effective February 9, 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; certificated in any category; equipped with 
Pratt & Whitney JT9D-3, and -7 (except -70) series engines or 
General Electric CF6-50 series engines with modified JT9D-7 inboard 
struts; as listed in Boeing Alert Service Bulletin 747-54A2219, 
dated September 4, 2003.

Unsafe Condition

    (d) This AD was prompted by reports of cracking in the midspar 
web. We are issuing this AD to detect and correct cracking in the 
midspar assembly, which could result in the loss of the midspar 
assembly load path, and could, combined with the loss of the nacelle 
station 180 bulkhead load path, lead to the separation of the engine 
from 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.

Compliance Times

    (f) Within 18 months after the effective date of this AD, do the 
actions in paragraphs (g) and (h) of this AD, as applicable. Repeat 
the actions thereafter at intervals not to exceed 1,200 flight 
cycles.

Inboard Strut Midspar Inspection

    (g) For Group 1 and 2 airplanes specified in paragraph 1.A.1. of 
Boeing Alert Service Bulletin 747-54A2219, dated September 4, 2003: 
Perform a detailed inspection of the midspar web of the inboard 
struts for cracking, disbonding, or buckling; a detailed inspection 
of the midspar stiffeners for any crack or fracture; related 
investigative actions; and any applicable corrective actions; in 
accordance with ``Part 1'' of the Work Instructions of Boeing Alert 
Service Bulletin 747-54A2219, dated September 4, 2003; except as 
required by paragraph (i) of this AD. Perform any related 
investigative actions and any applicable corrective actions before 
further flight.

Outboard Strut Midspar Inspection

    (h) For Group 1 airplanes specified in paragraph 1.A.1. of 
Boeing Alert Service Bulletin 747-54A2219, dated September 4, 2003: 
Perform a detailed inspection of the midspar web of the outboard 
struts for cracking, disbonding, or buckling; a detailed inspection 
of the midspar stiffeners for any crack or fracture; related 
investigative actions; and any applicable corrective actions; in 
accordance with ``Part 2'' of the Work Instructions of Boeing Alert 
Service Bulletin 747-54A2219, dated September 4, 2003; except as 
required by paragraph (i) of this AD. Perform any related 
investigative actions and any applicable corrective actions before 
further flight.

Contact the FAA/Designated Engineering Representative (DER)

    (i) Where Boeing Alert Service Bulletin 747-54A2219, dated 
September 4, 2003, specifies to contact Boeing for appropriate 
action: Before further flight, repair per a method approved by the 
Manager, Seattle Aircraft Certification Office (ACO), FAA; or per 
data meeting the type certification basis of the airplane approved 
by a Boeing Company DER who has been authorized by the Manager, 
Seattle ACO, to make such findings. For a repair method to be 
approved, the approval must specifically reference this AD.

Alternative Methods of Compliance (AMOCs)

    (j)(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 a 
Boeing Company DER who has been authorized by the Manager, Seattle 
ACO, to make those findings. For a repair method to be approved, the 
approval must specifically refer to this AD.

Material Incorporated by Reference

    (k) You must use Boeing Alert Service Bulletin 747-54A2219, 
dated September 4, 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 http://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 December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-105 Filed 1-4-05; 8:45 am]
BILLING CODE 4910-13-P