Airworthiness Directives; Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F Series Airplanes, 56860-56862 [05-19239]
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<![CDATA[
56860
Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(h)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Related Information
(i) Brazilian airworthiness directive 2005–
08–05, effective September 6, 2005, also
addresses the subject of this AD.
Issued in Renton, Washington, on
September 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19238 Filed 9–28–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22526; Directorate
Identifier 2005–NM–008–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 747–200F, 747–200C, 747–400,
747–400D, and 747–400F Series
Airplanes
for sending your comments
electronically.
• Government-wide rulemaking Web
Site: Go to https://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.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207.
You can examine the contents of this
AD docket on the Internet at https://
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–2005–
22526; the directorate identifier for this
docket is 2005–NM–008–AD.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
AGENCY:
Comments Invited
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for all
Boeing Model 747–200F, 747–200C,
747–400, 747–400D, and 747–400F
series airplanes. This proposed AD
would require repetitive inspections for
cracking of certain fuselage internal
structure, and repair if necessary. This
proposed AD is prompted by fatigue
tests and analysis that identified areas of
the fuselage where fatigue cracks can
occur. We are proposing this AD to
prevent loss of the structural integrity of
the fuselage, which could result in rapid
depressurization of the airplane.
DATES: We must receive comments on
this proposed AD by November 14,
2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web Site: Go to https://
dms.dot.gov and follow the instructions
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–22526; Directorate Identifier
2005–NM–008–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 https://
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,
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
VerDate Aug<31>2005
16:16 Sep 28, 2005
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Fmt 4702
Sfmt 4702
business, labor union, etc.). You can
review DOT’s complete Privacy Act
Statement in the Federal Register
published on April 11, 2000 (65 FR
19477–78), or you can visit https://
dms.dot.gov.
Examining the Docket
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 DOT
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
Discussion
Boeing has completed extended
pressure fatigue tests on a Boeing Model
747SR and a 747–400 fuselage test
article. Boeing has also used updated
analysis methods on the 747 fuselage
structure. The tests and analysis have
identified areas of the fuselage where
fatigue cracks can occur. This condition,
if not corrected, could result in loss of
the structural integrity of the fuselage
and consequent rapid depressurization
of the airplane.
Related AD
On May 14, 2002, we issued AD
2002–10–10, amendment 39–12756 (67
FR 36081, May 23, 2002). That AD
applies to certain Boeing Model 747
airplanes. That AD requires repetitive
inspections to detect cracks in various
areas of the fuselage internal structure,
and repair if necessary. This proposed
AD would require similar inspections
for Model 747 airplanes that are not
identified in the applicability of AD
2002–10–10.
We also issued AD 2004–07–22,
amendment 39–13566 (69 FR 18250,
April 7, 2004), as corrected (69 FR
19618, April 13, 2005), and as further
corrected (69 FR 24063, May 3, 2005).
That AD applies to all Boeing Model
747 series airplanes and requires that
the FAA-approved maintenance
inspection program be revised to
include inspections that will give no
less than the required damage tolerance
rating for each structural significant
item, and repair of cracked structure.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 747–53A2500, dated
December 21, 2004. Procedures for
repetitive inspections for cracks are
listed in the following table:
E:\FR\FM\29SEP1.SGM
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Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Proposed Rules
56861
SERVICE BULLETIN PROCEDURES
The service bulletin describes procedures for—
Of the—
Internal detailed inspections .....................................................................
Upper deck floor beams;
Section 42 frames;
Section 46 frames; and
Nose wheel well bulkheads, sidewall panels, and the STA 360 and 380
main deck floor beams.
Main entry doors and door cutouts; and
Fuselage skin at all four corners of the main electronics bay access
door cutout.
Internal and external detailed inspections ................................................
The compliance threshold is 22,000 or
25,000 total flight cycles (depending on
the inspection area and airplane
configuration), with a repetitive interval
of 3,000 flight cycles. The service
bulletin recommends repairing cracks
by using the structural repair manual
(SRM) or contacting Boeing.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition.
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
accomplishing the actions specified in
the service information described
previously, except as discussed below.
Differences Between the Proposed AD
and the Service Bulletin
The service bulletin specifies
compliance times relative to the date of
issuance of the service bulletin;
however, this proposed AD would
require compliance before the specified
compliance times relative to the
effective date of this AD.
Also, the service bulletin specifies
contacting the manufacturer for
instructions on how to repair certain
conditions, but this proposed AD would
require you to repair those conditions
by using a method that we approve, or
using data that meet the certification
basis of the airplane and that have been
approved by an Authorized
Representative for the Boeing Delegation
Option Authorization Organization
whom we have authorized to make
those findings.
Costs of Compliance
There are about 706 airplanes of the
affected design in the worldwide fleet.
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
ESTIMATED COSTS
(per inspection cycle)
Action
Work
hours
Inspections ................................
Average labor
rate per hour
260
$65
None required ...........................
Authority for This Rulemaking
Regulatory Findings
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.
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
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Number of
U.S.-registered
airplanes
Cost per
airplane
Parts
$16,900
107
Fleet cost
$1,808,300
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
Boeing: Docket No. FAA–2005–22526;
Directorate Identifier 2005–NM–008–AD.
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56862
Federal Register / Vol. 70, No. 188 / Thursday, September 29, 2005 / Proposed Rules
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this AD
action by November 14, 2005.
Affected ADs
(b) Inspections specified in this AD may be
considered an alternative method of
compliance (AMOC) for certain requirements
of AD 2004–07–22, as specified in paragraph
(i)(2) of this AD.
Applicability
(c) This AD applies to all Boeing Model
747–200F, 747–200C, 747–400, 747–400D,
and 747–400F series airplanes; certificated in
any category.
Unsafe Condition
(d) This AD was prompted by fatigue tests
and analysis that identified areas of the
fuselage where fatigue cracks can occur. We
are issuing this AD to prevent loss of the
structural integrity of the fuselage, which
could result in rapid depressurization 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.
Inspections
(f) Except as required/provided by
paragraphs (g) and (h) of this AD: Do initial
and repetitive inspections for fuselage cracks
using applicable internal and external
detailed inspection methods, and repair all
cracks, by doing all the actions specified in
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2500, dated
December 21, 2004. Do the initial and
repetitive inspections at the times specified
in paragraph 1.E. of the service bulletin.
Repair any crack before further flight after
detection.
Exceptions to Service Bulletin Procedures
(g) If any crack is found during any
inspection required by this AD, and the
bulletin specifies to contact Boeing for
appropriate action: Before further flight,
repair the crack according to a method
approved by the Manager, Seattle Aircraft
Certification Office (ACO), FAA; or according
to 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
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically reference this AD.
(h) Where the service bulletin specifies a
compliance time after the issuance of the
service bulletin, this AD requires compliance
within the specified compliance time after
the effective date of this AD.
AMOCs
(i)(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
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(2) Accomplishment of the inspections
specified in this AD is considered an AMOC
for the applicable requirements of paragraphs
(c) and (d) of AD 2004–07–22, amendment
39–13566, under the following conditions:
(i) The actions must be done within the
compliance times specified in AD 2004–07–
22. The initial inspection must be done at the
times specified in paragraph (d) of AD 2004–
07–22, and the inspections must be repeated
within the intervals specified in paragraph (f)
of this AD.
(ii) The AMOC applies only to the areas of
Supplemental Structural Inspection
Document D6–35022, Revision G, that are
specified in Boeing Alert Service Bulletin
747–53A2500, dated December 21, 2004.
(3) 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.
(4) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Issued in Renton, Washington, on
September 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–19239 Filed 9–28–05; 8:45 am]
however, these companies would
continue to file their quarterly reports
on Form 10–Q under the current 40-day
deadline, rather than the 35-day
deadline that was scheduled to apply to
quarterly reports filed next year. Other
accelerated filers would continue to file
both their annual and quarterly reports
under current deadlines—75 days after
fiscal year end for annual reports on
Form 10–K and 40 days after quarter
end for quarterly reports on Form 10–Q.
We also are proposing to revise the
definition of the term ‘‘accelerated filer’’
to permit an accelerated filer that has
voting and non-voting common equity
held by non-affiliates of less than $25
million to exit accelerated filer status
promptly and begin filing its annual and
quarterly reports on a non-accelerated
filer basis. Finally, the proposed
amendments would permit a large
accelerated filer that has voting and
non-voting common equity held by nonaffiliates of less than $75 million to
promptly exit large accelerated filer
status.
Comments should be received on
or before October 31, 2005.
ADDRESSES: Comments may be
submitted by any of the following
methods:
DATES:
Electronic Comments
17 CFR Parts 210, 229, 240 and 249
• Use the Commission’s Internet
comment form https://www.sec.gov/
rules/proposed.shtml; or
• Send an e-mail to rulecomments@sec.gov. Please include File
Number S7–08–05 on the subject line;
or
• Use the Federal eRulemaking Portal
(https://www.regulations.gov). Follow the
instructions for submitting comments.
[Release Nos. 33–8617; 34–52491; File No.
S7–08–05]
Paper Comments
BILLING CODE 4910–13–P
SECURITIES AND EXCHANGE
COMMISSION
RIN 3235–AJ29
Revisions to Accelerated Filer
Definition and Accelerated Deadlines
for Filing Periodic Reports
Securities and Exchange
Commission.
ACTION: Proposed rule.
AGENCY:
SUMMARY: We are proposing to modify
the periodic report filing deadlines so
that only the largest accelerated filers
(those with a market value of
outstanding voting and non-voting
common equity held by non-affiliates of
$700 million or more) become subject to
the final phase-in of the accelerated
filing transition schedule that will
require annual reports on Form 10–K to
be filed within 60 days after fiscal year
end. Under our proposed amendments,
PO 00000
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• Send paper comments in triplicate
to Jonathan G. Katz, Secretary,
Securities and Exchange Commission,
100 F Street, NE, Washington, DC
20549–9303.
All submissions should refer to File
Number S7–08–05. This file number
should be included on the subject line
if e-mail is used. To help us process and
review your comments more efficiently,
please use only one method. The
Commission will post all comments on
the Commission’s Internet Web site
(https://www.sec.gov/rules/
proposed.shtml). Comments will also be
available for public inspection and
copying in the Commission’s Public
Reference Room, 100 F Street, NE,
Washington, DC 20549. All comments
received will be posted without change;
we do not edit personal identifying
information from submissions. You
E:\FR\FM\29SEP1.SGM
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]]>Agencies
[Federal Register Volume 70, Number 188 (Thursday, September 29, 2005)]
[Proposed Rules]
[Pages 56860-56862]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19239]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22526; Directorate Identifier 2005-NM-008-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-200F, 747-200C, 747-
400, 747-400D, and 747-400F Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-
400F series airplanes. This proposed AD would require repetitive
inspections for cracking of certain fuselage internal structure, and
repair if necessary. This proposed AD is prompted by fatigue tests and
analysis that identified areas of the fuselage where fatigue cracks can
occur. We are proposing this AD to prevent loss of the structural
integrity of the fuselage, which could result in rapid depressurization
of the airplane.
DATES: We must receive comments on this proposed AD by November 14,
2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web Site: Go to https://
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.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207.
You can examine the contents of this AD docket on the Internet at
https://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-2005-22526; the directorate identifier for this docket is
2005-NM-008-AD.
FOR FURTHER INFORMATION CONTACT: 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.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22526;
Directorate Identifier 2005-NM-008-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 https://
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 can review DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
can visit https://dms.dot.gov.
Examining the Docket
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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the DMS receives them.
Discussion
Boeing has completed extended pressure fatigue tests on a Boeing
Model 747SR and a 747-400 fuselage test article. Boeing has also used
updated analysis methods on the 747 fuselage structure. The tests and
analysis have identified areas of the fuselage where fatigue cracks can
occur. This condition, if not corrected, could result in loss of the
structural integrity of the fuselage and consequent rapid
depressurization of the airplane.
Related AD
On May 14, 2002, we issued AD 2002-10-10, amendment 39-12756 (67 FR
36081, May 23, 2002). That AD applies to certain Boeing Model 747
airplanes. That AD requires repetitive inspections to detect cracks in
various areas of the fuselage internal structure, and repair if
necessary. This proposed AD would require similar inspections for Model
747 airplanes that are not identified in the applicability of AD 2002-
10-10.
We also issued AD 2004-07-22, amendment 39-13566 (69 FR 18250,
April 7, 2004), as corrected (69 FR 19618, April 13, 2005), and as
further corrected (69 FR 24063, May 3, 2005). That AD applies to all
Boeing Model 747 series airplanes and requires that the FAA-approved
maintenance inspection program be revised to include inspections that
will give no less than the required damage tolerance rating for each
structural significant item, and repair of cracked structure.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2500, dated
December 21, 2004. Procedures for repetitive inspections for cracks are
listed in the following table:
[[Page 56861]]
Service Bulletin Procedures
------------------------------------------------------------------------
The service bulletin describes
procedures for-- Of the--
------------------------------------------------------------------------
Internal detailed inspections.......... Upper deck floor beams;
Section 42 frames;
Section 46 frames; and
Nose wheel well bulkheads,
sidewall panels, and the STA
360 and 380 main deck floor
beams.
Internal and external detailed Main entry doors and door
inspections. cutouts; and
Fuselage skin at all four
corners of the main
electronics bay access door
cutout.
------------------------------------------------------------------------
The compliance threshold is 22,000 or 25,000 total flight cycles
(depending on the inspection area and airplane configuration), with a
repetitive interval of 3,000 flight cycles. The service bulletin
recommends repairing cracks by using the structural repair manual (SRM)
or contacting Boeing. Accomplishing the actions specified in the
service information is intended to adequately address the unsafe
condition.
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 accomplishing the actions specified in the service
information described previously, except as discussed below.
Differences Between the Proposed AD and the Service Bulletin
The service bulletin specifies compliance times relative to the
date of issuance of the service bulletin; however, this proposed AD
would require compliance before the specified compliance times relative
to the effective date of this AD.
Also, the service bulletin specifies contacting the manufacturer
for instructions on how to repair certain conditions, but this proposed
AD would require you to repair those conditions by using a method that
we approve, or using data that meet the certification basis of the
airplane and that have been approved by an Authorized Representative
for the Boeing Delegation Option Authorization Organization whom we
have authorized to make those findings.
Costs of Compliance
There are about 706 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this proposed AD.
Estimated Costs
(per inspection cycle)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work Average labor Parts Cost per registered Fleet cost
hours rate per hour airplane airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections.................................. 260 $65 None required................... $16,900 107 $1,808,300
--------------------------------------------------------------------------------------------------------------------------------------------------------
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 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-2005-22526; Directorate Identifier 2005-NM-
008-AD.
[[Page 56862]]
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this AD action by November 14, 2005.
Affected ADs
(b) Inspections specified in this AD may be considered an
alternative method of compliance (AMOC) for certain requirements of
AD 2004-07-22, as specified in paragraph (i)(2) of this AD.
Applicability
(c) This AD applies to all Boeing Model 747-200F, 747-200C, 747-
400, 747-400D, and 747-400F series airplanes; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by fatigue tests and analysis that
identified areas of the fuselage where fatigue cracks can occur. We
are issuing this AD to prevent loss of the structural integrity of
the fuselage, which could result in rapid depressurization 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.
Inspections
(f) Except as required/provided by paragraphs (g) and (h) of
this AD: Do initial and repetitive inspections for fuselage cracks
using applicable internal and external detailed inspection methods,
and repair all cracks, by doing all the actions specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2500, dated December 21, 2004. Do the initial and repetitive
inspections at the times specified in paragraph 1.E. of the service
bulletin. Repair any crack before further flight after detection.
Exceptions to Service Bulletin Procedures
(g) If any crack is found during any inspection required by this
AD, and the bulletin specifies to contact Boeing for appropriate
action: Before further flight, repair the crack according to a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or according to 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 method to be approved, the repair must meet the
certification basis of the airplane, and the approval must
specifically reference this AD.
(h) Where the service bulletin specifies a compliance time after
the issuance of the service bulletin, this AD requires compliance
within the specified compliance time after the effective date of
this AD.
AMOCs
(i)(1) The Manager, Seattle Aircraft Certification Office (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) Accomplishment of the inspections specified in this AD is
considered an AMOC for the applicable requirements of paragraphs (c)
and (d) of AD 2004-07-22, amendment 39-13566, under the following
conditions:
(i) The actions must be done within the compliance times
specified in AD 2004-07-22. The initial inspection must be done at
the times specified in paragraph (d) of AD 2004-07-22, and the
inspections must be repeated within the intervals specified in
paragraph (f) of this AD.
(ii) The AMOC applies only to the areas of Supplemental
Structural Inspection Document D6-35022, Revision G, that are
specified in Boeing Alert Service Bulletin 747-53A2500, dated
December 21, 2004.
(3) 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.
(4) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
Issued in Renton, Washington, on September 16, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-19239 Filed 9-28-05; 8:45 am]
BILLING CODE 4910-13-P
