[Federal Register: December 9, 2004 (Volume 69, Number 236)]
[Rules and Regulations]
[Page 71349-71351]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09de04-6]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19811; Directorate Identifier 2004-NM-201-AD;
Amendment 39-13893; AD 2004-25-05]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-
200C, 747-200F, 747-300, 747SP, and 747SR series airplanes. This AD
requires repetitive inspections to detect cracks and fractures of the
strut front spar chord assembly at each strut location, and repair if
necessary. This AD is prompted by a report of a fractured front spar
chord assembly for strut No. 3, which resulted in the loss of the strut
upper link load path. We are issuing this AD to prevent loss of the
strut upper link load path and consequent fracture of the diagonal
brace, which could result in in-flight separation of the strut and
engine from the airplane.
DATES: Effective December 27, 2004.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of
December 27, 2004.
We must receive comments on this AD by February 7, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street SW., Nassif Building, room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street SW., Washington, DC, between 9:00
a.m. and 5:00 p.m., Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, PO 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-2004-19811; the directorate identifier for this docket is
2004-NM-201-AD.
Docket Management System (DMS)
The FAA has implemented new procedures for maintaining AD dockets
electronically. As of May 17, 2004, new AD actions are posted on DMS
and assigned a docket number. We track each action and assign a
corresponding directorate identifier. The DMS AD docket number is in
the form ``Docket No. FAA-2004-99999.'' The Transport Airplane
Directorate identifier is in the form ``Directorate Identifier 2004-NM-
999-AD.'' Each DMS AD docket also lists the directorate identifier
(``Old Docket Number'') as a cross-reference for searching purposes.
Examining the Dockets
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. Comments will be
available in the AD docket shortly after the DMS receives them.
FOR FURTHER INFORMATION CONTACT: Technical information: 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. Plain language
information: Marcia Walters, marcia.walters@faa.gov.
SUPPLEMENTARY INFORMATION: We have received a report indicating that
the front spar chord assembly for strut No. 3 fractured on a Boeing
Model 747-200B series airplane that had accumulated a total of 16,604
flight cycles and 79,013 flight hours. The front spar chord assembly
fractured 4.37 inches forward of the upper link attach lug. The
manufacturer's analysis showed that the fitting fractured as the result
of fatigue at a critical stress area. Fracture of the front spar chord
assembly will result in the loss of the strut upper link load path.
Loss of the upper link load path would result in the transfer of
additional loads to the diagonal brace load path, which could result in
fracture of the diagonal brace. This condition, if not corrected, could
result in in-flight separation of the strut and engine from the
airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin (ASB) 747-54A2224,
dated September 30, 2004. The ASB describes procedures for
accomplishing detailed and high frequency eddy current (HFEC)
inspections of the strut front spar chord assembly for cracks and
fractures at each strut location. The ASB also specifies, if any crack
or fracture is found, to contact the manufacturer for additional
instructions and repair. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other airplanes of the same type design. Therefore, we are
issuing this AD to prevent loss of the strut upper link load path and
consequent fracture
[[Page 71350]]
of the diagonal brace, which could result in in-flight separation of
the strut and engine from the airplane. This AD requires accomplishing
the actions specified in the service information described previously,
except as discussed under ``Difference Between the AD and the ASB.''
Difference Between the AD and the ASB
The ASB specifies that you may contact the manufacturer for
instructions on how to repair certain conditions, but this AD requires
you to repair those conditions in one of the following ways:
Using a method that we approve; or
Using data that meet the type certification basis of the
airplane, and that have been approved by a Boeing Company Designated
Engineering Representative who has been authorized by the FAA to make
those findings.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD; therefore, providing notice and opportunity for public comment
before the AD is issued is impracticable, and good cause exists to make
this AD effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any relevant written
data, views, or arguments regarding this AD. Send your comments to an
address listed under ADDRESSES. Include ``Docket No. FAA-2004-19811;
Directorate Identifier 2004-NM-201-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of our docket
web site, anyone can find and read the comments in any of our dockets,
including the name of the individual who sent the comment (or signed
the comment on behalf of an association, business, labor union, etc.).
You can review the DOT's complete Privacy Act Statement in the Federal
Register published on April 11, 2000 (65 FR 19477-78), or you can visit
http://dms.dot.gov.
We are reviewing the writing style we currently use in regulatory
documents. We are interested in your comments on whether the style of
this document is clear, and your suggestions to improve the clarity of
our communications with you. You can get more information about plain
language at http://www/faa.gov/language and http://www.plainlanguage.gov.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 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):
2004-25-05 Boeing: Amendment 39-13893. Docket No. FAA-2004-19811;
Directorate Identifier 2004-NM-201-AD.
Effective Date
(a) This AD becomes effective December 27, 2004.
Applicability
(b) This AD applies to Boeing 747-100, 747-100B, 747-100B SUD,
747-200B, 747-200C, 747-200F, 747-300, 747SP, and 747SR series
airplanes; as listed in Boeing Alert Service Bulletin (ASB) 747-
54A2224, dated September 30, 2004; certificated in any category.
Unsafe Condition
(c) This AD was prompted by a report of a fractured front spar
chord assembly for strut No. 3, which resulted in the loss of the
strut upper link load path. The FAA is issuing this AD to prevent
loss of the strut upper link load path and consequent fracture of
the diagonal brace, which could result in in-flight separation of
the strut and engine.
Compliance
(d) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Detailed and High Frequency Eddy Current (HFEC) Inspections
(e) Within 90 days after the effective date of this AD, perform
detailed and HFEC inspections to detect any cracks or fractures of
the front spar chord assembly for struts Number 1 through 4
inclusive, in accordance with Boeing ASB 747-54A2224, dated
September 30, 2004.
(f) Accomplishment of the detailed and HFEC inspections in
accordance with Boeing 747 Fleet Team Digest 747-FTD-54-04002, dated
April 15, 2004, May 4, 2004, June 1, 2004, July 12, 2004, or July
28, 2004; or Boeing Message 1-C6ELC (Service Request ID No.:
218724992), dated April 14, 2004; before the effective date of this
AD, is considered acceptable for compliance with the requirements of
paragraph (e) of this AD.
Repetitive Inspections
(g) For airplanes on which no crack or fracture is detected: At
the times specified in Table 1--Repetitive Intervals of this AD,
perform the detailed and HFEC inspections required by paragraph (e)
of this AD at the intervals specified in Table 1.
Table 1.--Repetitive Intervals
------------------------------------------------------------------------
For Airplanes identified in Boeing ASB
747-54A2224, dated September 30, 2004, At intervals not to exceed--
as--
------------------------------------------------------------------------
Group 1................................ 1,000 flight cycles or 18
months, whichever occurs
first.
Group 2 and Group 3.................... 1,200 flight cycles or 18
months, whichever occurs
first.
Group 4 and Group 6.................... 1,500 flight cycles or 18
months, whichever occurs
first.
Group 5................................ 2,000 flight cycles or 18
months, whichever occurs
first.
------------------------------------------------------------------------
[[Page 71351]]
Corrective Action
(h) If any crack or fracture is found during any inspection
required by this AD, and the bulletin specifies contacting Boeing
for appropriate action: Before further flight, repair the crack or
fracture according to 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 Designated Engineering Representative (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
reference this AD.
Alternative Methods of Compliance (AMOCs)
(i)(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
(j) You must use Boeing Alert Service Bulletin 747-54A2224,
dated September 30, 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. For
copies of the service information, contact Boeing Commercial
Airplanes, PO Box 3707, Seattle, Washington 98124-2207. You can
review copies at the Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW., room PL-401, Nassif
Building, Washington, DC; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Issued in Renton, Washington, on November 30, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-26793 Filed 12-8-04; 8:45 am]
BILLING CODE 4910-13-P