[Federal Register: December 20, 2005 (Volume 70, Number 243)]
[Proposed Rules]
[Page 75426-75428]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20de05-24]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-23358; Directorate Identifier 2005-NM-206-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain 747-100, -200, and -300 series
airplanes. The existing AD currently requires repetitive inspections to
detect cracking of certain lower lobe fuselage frames, and repair if
necessary. This proposed AD would retain all the requirements of the
existing AD, and add airplanes to the applicability. This proposed AD
results from reports indicating that fatigue cracks were found in lower
lobe frames on the left side of the fuselage. We are proposing this AD
to detect and correct fatigue cracking of certain lower lobe fuselage
frames, which could lead to fatigue cracks in the fuselage skin, and
consequent rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by February 3,
2006.
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.
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.
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle,
Washington 98124-2207, for service information identified in this
proposed 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 in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2005-23358; Directorate Identifier 2005-NM-206-AD'' at the
beginning 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 received 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 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.
Examining the Docket
You may 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 Docket Management System
receives them.
Discussion
On March 22, 1999, we issued AD 99-07-12, amendment 39-11097 (64 FR
15298, March 31, 1999), for certain Boeing Model 747-100, -200, and -
300 series airplanes. That AD requires repetitive inspections to detect
cracking of certain lower lobe fuselage frames, and repair if
necessary. That AD resulted from reports indicating that fatigue cracks
were found in lower lobe frames on the left side of the fuselage. We
issued that AD to detect and correct fatigue cracking of certain lower
lobe fuselage frames, which could lead to fatigue cracks in the
fuselage skin, and consequent rapid decompression of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 99-07-12, the manufacturer has issued new
service information that expands the applicability to include 747-400
and -400D series airplanes, line numbers 696 to 1152 inclusive.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2408,
Revision 1, dated April 4, 2002 (the original revision of that alert
service bulletin, dated April 25, 1996, was referenced as the
appropriate source of service information for accomplishing the
required actions in AD 99-07-12). The procedures in Revision 1 of the
alert service bulletin are essentially the same as the procedures in
the original revision for the airplanes affected by AD 99-07-12
(identified in the service bulletin as Group 1 airplanes). These
procedures include repetitive inspections to detect cracking of certain
lower lobe fuselage frames, and repair if necessary. For the 747-400
and -400D series airplanes that are added to the effectivity of the
service bulletin (identified as Group 2 airplanes), the service
bulletin specifies contacting the manufacturer for information about
how to repair frames that have crack damage.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 99-07-12 and would retain the requirements of the
existing AD. This proposed AD also would add airplanes to the
applicability and require accomplishing the actions specified in the
service bulletin described previously, except as discussed under
``Difference Between
[[Page 75427]]
the Proposed AD and the Service Bulletin.''
Difference Between the Proposed AD and the Service Bulletin
The service bulletin specifies to contact the manufacturer for
instructions on how to repair certain conditions, but this proposed AD
would require repairing those conditions in one of the following ways:
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 Commercial Airplanes Delegation Option Authorization
Organization whom we have authorized to make those findings.
Explanation of Change to Applicability
We have revised the applicability of the AD to identify the model
designations as published in the most recent type certificate data
sheet for the affected model.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Clarification of Inspection Terminology
In this proposed AD, the ``detailed visual inspection'' specified
in the Boeing service bulletin is referred to as a ``detailed
inspection.'' We have also changed references to a ``detailed visual
inspection'' in the existing AD to refer to a ``detailed inspection.''
We have included the definition for a detailed inspection in a note in
the proposed AD.
Explanation of Change to Certain References to Other AD
AD 99-07-12 refers to AD 93-08-12 amendment 39-8559 (58 FR 27927,
May 12, 1993), in the section titled ``Interim Action,'' and in
paragraphs (a) and (d), and Note 3 of that AD. Since we issued AD 99-
07-12 we have superseded AD 93-08-12 with AD 2005-20-30 amendment 39-
14327 (70 FR 59252, October 12, 2005). Therefore, this proposed AD
refers to AD 2005-20-30 rather than to AD 93-08-12.
Changes to Paragraph Identifiers in Existing AD
This proposed AD would retain all requirements of AD 99-07-12.
Since AD 99-07-12 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
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Corresponding requirement
Requrement in AD 99-07-12 in this proposed AD
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Paragraph (a)............................. Paragraph (f).
Paragraph (b)............................. Paragraph (g).
Paragraph (c)............................. Paragraph (h).
Paragraph (d)............................. Paragraph (i).
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Interim Action
This is considered to be interim action only until the
accomplishment of AD 2005-20-30 for Boeing Model 747-100, 747-100B,
747-100B SUD, 747-200B, and 747-300, and 747SR series airplanes. AD
2005-20-30 requires a detailed inspection to detect cracks in the
Section 46 lower lobe frames, and repair if necessary, in accordance
with Boeing Service Bulletin 747-53-2349, Revision 2, dated April 3,
2003. The initial inspection required by AD 2005-20-30 is required
prior to the accumulation of 22,000 total flight cycles. We find that
earlier inspection (i.e., prior to accumulation of 15,000 total flight
cycles) of the lower lobe frames is warranted, as proposed by this AD.
This is also considered to be interim action for Boeing Model 747-
400 and 747-400D airplanes only until the accomplishment of an action
similar to AD 2005-20-30 for these airplanes. On September 16, 2005, we
issued NPRM Docket No. FAA-2005-22526 (70 FR 56860, September 29,
2005), Directorate Identifier 2005-NM-008-AD. That NPRM proposes to
require repetitive inspections for cracking of certain fuselage
internal structure, and repair if necessary.
Costs of Compliance
There are about 681 airplanes of the affected design in the
worldwide fleet. This proposed AD would affect about 99 airplanes of
U.S. registry.
The actions that are required by AD 99-07-12 and retained in this
proposed AD take about 2 work hours per airplane, at an average labor
rate of $65 per work hour. Based on these figures, the estimated cost
of both the retained and proposed actions for U.S. operators is
$12,870, or $130 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 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 and placed it in the AD docket. 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 Federal Aviation Administration (FAA) amends Sec. 39.13
[[Page 75428]]
by removing amendment 39-11097 (64 FR 15298, March 31, 1999) and adding
the following new airworthiness directive (AD):
Boeing: Docket No. FAA-2005-23358; Directorate Identifier 2005-NM-
206-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by February
3, 2006.
Affected ADs
(b) This AD supersedes AD 99-07-12.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR series
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin 747-53A2408, Revision 1, dated April 4, 2002.
Unsafe Condition
(d) This AD results from reports indicating that fatigue cracks
were found in lower lobe frames on the left side of the fuselage. We
are issuing this AD to detect and correct fatigue cracking of
certain lower lobe fuselage frames, which could lead to fatigue
cracks in the fuselage skin, and consequent rapid decompression 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.
Restatement of the Requirements of AD 99-07-12, With Additional
Information for Group 2 Airplanes
Initial Inspections
(f) For airplanes on which the initial detailed internal
inspection of the Section 46 lower lobe frames required by paragraph
(f)(2) or (i)(2) of AD 2005-20-30, amendment 39-14327, has not been
accomplished: Perform a detailed visual inspection to detect
cracking of the lower lobe fuselage frames from Body Station 1820 to
Body Station 2100, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2408, dated
April 25, 1996; or Boeing Alert Service Bulletin 747-53A2408,
Revision 1, dated April 4, 2002; as applicable; at the later of the
applicable times specified in paragraph (f)(1), (f)(2), or (f)(3) of
this AD.
(1) For all airplanes: Prior to the accumulation of 15,000 total
flight cycles; or
(2) For Group 1 airplanes identified in Revision 1 of the
service bulletin: Within 1,500 flight cycles or 18 months after May
5, 1999 (the effective date of AD 99-07-12), whichever occurs first.
(3) For Group 2 airplanes identified in Revision 1 of the
service bulletin: Within 1,500 flight cycles or 18 months after the
effective date of this AD, whichever occurs first.
Note 1: Paragraph (f)(2) or (i)(2) of AD 2005-20-30 requires a
detailed inspection to detect cracks in the Section 46 lower lobe
frames, in accordance with Boeing Service Bulletin 747-53-2349,
Revision 2, dated April 3, 2003. The initial inspection is required
prior to the accumulation of 22,000 total flight cycles; or within
1,000 flight cycles after June 11, 1993 (the effective date of AD
93-08-12, amendment 39-8559), or November 16, 2005 (the effective
date of AD 2005-20-30), depending on previous inspections
accomplished; whichever occurs later.
Note 2: 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
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Repetitive Inspections
(g) If no cracking is detected during the inspection required by
paragraph (f) of this AD, repeat the inspection thereafter at
intervals not to exceed 3,000 flight cycles.
Corrective Actions
(h) If any cracking is detected during any inspection required
by paragraph (f) of this AD, prior to further flight, accomplish
paragraphs (h)(1) and (h)(2) of this AD:
(1) Within 20 inches of the crack location on the frame, perform
a detailed inspection of the adjacent structure to detect cracking.
If any cracking is detected during any detailed inspection done in
accordance with paragraph (f) or (h)(1) of this AD, prior to further
flight, repair in accordance with paragraph (h)(1)(i) or (h)(1)(ii)
of this AD, as applicable.
(i) For Group 1 airplanes: Using a method approved in accordance
with the procedures specified in paragraph (j) of this AD. The
Boeing 747 Structural Repair Manual, Subject 53-10-04, Figure 67 or
90, is one approved method.
(ii) For Group 2 airplanes: Using a method approved in
accordance with the procedures specified in paragraph (j) of this
AD.
(2) Repeat the inspection required by paragraph (f) of this AD
thereafter at intervals not to exceed 3,000 flight cycles.
Optional Terminating Inspection
(i) Accomplishment of the initial detailed inspection of the
Section 46 lower lobe frames required by paragraph (f)(2) or (i)(2)
of AD 2005-20-30 constitutes terminating action for the requirements
of this AD only for airplanes identified in Boeing Alert Service
Bulletin 747-53A2408, Revision 1, dated April 4, 2002, as Group 1
airplanes.
Alternative Methods of Compliance (AMOCs)
(j)(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) 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.
(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 Commercial Airplanes
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.
(4) AMOCs approved previously in accordance with AD 99-07-12,
amendment 39-11097, are approved as AMOCs for the corresponding
provisions of this AD.
Issued in Renton, Washington, on December 13, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 05-24242 Filed 12-19-05; 8:45 am]
BILLING CODE 4910-13-P