[Federal Register: August 6, 2004 (Volume 69, Number 151)]
[Proposed Rules]
[Page 47811-47813]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06au04-20]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18728; Directorate Identifier 2003-NM-176-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-400 and -400F Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain Boeing Model 747-400 and -400F series airplanes. This
proposed AD would require a detailed inspection(s) for cracks and
fractures of the side guide support fittings in the lower lobe cargo
compartments; and applicable investigative/corrective actions and
operational limitations, if necessary. This proposed AD also would
require a terminating action for the repetitive inspections. This
proposed AD is prompted by reports of cracked/fractured side guide
support fittings in the aft, lower lobe cargo compartment. We are
proposing this AD to prevent cracked/fractured side guide support
fittings in the lower lobe cargo compartments, which could result in
unrestrained cargo shifting in flight and damaging the airplane
structure or systems, and consequent reduced controllability of the
airplane.
DATES: We must receive comments on this proposed AD by September 20,
2004.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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.
By 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
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You can get the service information identified in this proposed AD
from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207.
You may examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or 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.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Airframe Branch, ANM-120S,
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056; telephone (425) 917-6437; fax (425) 917-
6590.
SUPPLEMENTARY INFORMATION:
[[Page 47812]]
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.
Comments Invited
We invite you to submit any written relevant data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2004-18728;
Directorate Identifier 2003-NM-176-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments submitted by the closing date and may amend the
proposed 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 proposed AD. Using the search function of
that 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 may review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may 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 that affect you. You can get more information about
plain language at http://www.faa.gov/language and http://www.plainlanguage.gov.Examining
the Docket
You may examine the AD docket 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.
Discussion
We have received two reports indicating that cracked/fractured side
guide support fittings were found in the aft, lower lobe cargo
compartment on Boeing Model 747-400F series airplanes that had been in
service less than 16 months. One airplane had a total of 16 cracked/
fractured side guide support fittings and the other airplane had 4. The
side guide support fittings provide lateral and vertical restraint for
cargo in the lower lobe cargo compartments.
Investigation revealed that failed roller assemblies in the
outboard roller trays caused the conveyor plane of the unit load device
(ULD) to drop and allowed the ULD to impact the side guide support
fittings. Repeated impacts by the ULD can result in fatigue and
consequent cracked/fractured side guide support fittings. The roller
assembly failures were caused by a manufacturing defect in the bearings
that resulted in the separation of the bearing's inner and outer race.
Cracked/fractured side guide support fittings in the lower lobe
cargo compartments, if not corrected, could result in unrestrained
cargo shifting in flight and damaging the airplane structure or systems
and consequent reduced controllability of the airplane.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-25A3335, dated
July 3, 2003. The service bulletin describes procedures for a detailed
inspection(s) for cracks and fractures of the side guide support
fittings in the lower lobe cargo compartments, and applicable
investigative/corrective actions and operational limitations, if
necessary. The applicable investigative actions include a general
visual inspection of the cargo compartment for damage, and repair if
necessary. The corrective actions include replacing cracked or
fractured side guide support fittings with new fittings; and replacing
all outboard roller assemblies with new assemblies, which would
eliminate the need for repetitive detailed inspections. The service
bulletin also describes operational limitations for missing restraints
until replacement of cracked or fractured side guide support fittings.
We have determined that accomplishing of the actions specified in the
service bulletin will adequately address the unsafe condition.
Boeing Alert Service Bulletin 747-25A3335 refers to Goodrich Alert
Service Bulletin 65B60176-25-A01, dated March 3, 2003, as an additional
source of service information for doing the replacement of the outboard
roller assemblies.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other airplanes
of this same type design. Therefore, we are proposing this AD, which
would require a detailed inspection(s) of the side guide support
fittings in the lower lobe cargo compartments for cracks and fractures;
and applicable investigative/corrective actions and operational
limitations, if necessary. This proposed AD also would require a
terminating action for the repetitive inspections. The proposed AD
would require you to use the service information described previously
to perform these actions, except as discussed under ``Difference
Between the Proposed AD and Service Bulletin.''
Difference Between the Proposed AD and Service Bulletin
Figures 1 and 2 of the referenced Boeing service bulletin specify a
general visual inspection of the cargo compartment for damage, and
repair if necessary. We have determined that those actions are not
necessary to adequately address the identified unsafe condition of this
AD. Therefore, this proposed AD would not require operators to do that
inspection and repair.
Costs of Compliance
This proposed AD would affect about 22 airplanes worldwide. The
following table provides the estimated costs for U.S. operators to
comply with this proposed AD.
[[Page 47813]]
Estimated Costs
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Number of U.S.-
Action Work hours Average labor Parts Cost per registered Fleet cost
rate per hour airplane airplanes
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Inspection, per inspection cycle........................ 5 $65 None $325* 3 $975*
Assembly replacement.................................... 25 $65 $3,402 $5,027 3 $15,081
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* Per inspection cycle.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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 proposed 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, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive (AD):
Boeing: Docket No. FAA-2004-18728; Directorate Identifier 2003-NM-
176-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by September 20, 2004.
Affected ADs
(b) None.
Applicability: (c) This AD applies to Boeing Model 747-400 and
``400F series airplanes, certificated in any category; as listed in
Boeing Alert Service Bulletin 747-25A3335, dated July 3, 2003.
Unsafe Condition
(d) This AD was prompted by reports of cracked/fractured side
guide support fittings in the aft, lower lobe cargo compartment. We
are issuing this AD to prevent cracked/fractured side guide support
fittings in the lower lobe cargo compartments, which could result in
unrestrained cargo shifting in flight and damaging the airplane
structure or systems, 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.
Inspection, Investigative/Corrective Actions, and Operational
Limitations
(f) At the applicable time(s) specified in Table 1 of this AD,
do a detailed inspection(s) of the side guide support fittings in
the lower lobe cargo compartments for cracks and fractures, and
before further flight, do all applicable investigative/corrective
actions and operational limitations, if necessary, by accomplishing
all the actions specified in Work Package 1 and Work Package 2 of
the Work Instructions of Boeing Alert Service Bulletin 747-25A3335,
dated July 3, 2003; except as required by paragraph (g) of this AD.
Replacement of all outboard roller assemblies with new assemblies in
accordance with Work Package 2 of the service bulletin ends the
repetitive inspections required by paragraph (f)(1) of this AD (Work
Package 1).
Table 1.--Compliance Times
------------------------------------------------------------------------
Initial compliance Repetitive
For-- time-- interval--
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(1) Work Package 1............... Within 180 days At intervals not
after the to exceed 180
effective date of days, until all
this AD. outboard roller
assemblies have
been replaced
per Work Package
2 of the service
bulletin.
(2) Work Package 2............... Within 18 months None.
after the
effective date of
this AD.
------------------------------------------------------------------------
Note 1: For the purposes of this AD, a detailed inspection is
``an intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirrors magnifying lenses, etc. may be necessary. Surface cleaning
and elaborate procedures may be required.''
Note 2: Boeing Alert Service Bulletin 747-25A3335 refers to
Goodrich Alert Service Bulletin 65B60176-25-A01, dated March 3,
2003, as an additional source of service information for replacing
the outboard roller assemblies.
Alternative Methods of Compliance (AMOCs)
(g) 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.
Issued in Renton, Washington, on July 29, 2004.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-17989 Filed 8-5-04; 8:45 am]
BILLING CODE 4910-13-P