[Federal Register: May 26, 2009 (Volume 74, Number 99)]
[Proposed Rules]
[Page 24712-24715]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26my09-9]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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[[Page 24712]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0477; Directorate Identifier 2008-NM-191-AD]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, -100B, -100B SUD,
-200B, and -300 Series Airplanes; and Model 747SP and 747SR Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Boeing Model 747 series
airplanes. The existing AD currently requires repetitive inspections to
detect cracks in various areas of the fuselage internal structure, and
related investigative/corrective actions if necessary. This proposed AD
would require additional repetitive inspections for cracking of certain
fuselage structure, and related investigative/corrective actions if
necessary. This proposed AD results from fatigue tests and analysis by
Boeing that identified areas of the fuselage where fatigue cracks can
occur. We are proposing this AD to prevent the 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 July 10, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1, fax 206-766-5680; e-mail me.boecom@boeing.com;
Internet https://www.myboeingfleet.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information
on the availability of this material at the FAA, call 425-227-1221 or
425-227-1152.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Ivan Li, Aerospace Engineer, Airframe
Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6437;
fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0477;
Directorate Identifier 2008-NM-191-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On September 26, 2005, we issued AD 2005-20-30, amendment 39-14327
(70 FR 59252, October 12, 2005), for certain Boeing Model 747 series
airplanes. That AD requires repetitive inspections to detect cracks in
various areas of the fuselage internal structure, and related
investigative/corrective actions if necessary. That AD resulted from
fatigue tests and analysis by Boeing that identified areas of the
fuselage where fatigue cracks can occur. We issued that AD to prevent
the loss of the structural integrity of the fuselage, which could
result in rapid depressurization of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2005-20-30, Boeing has conducted an additional
analysis that shows that Section 41 fuselage frames in the areas
attached to the upper deck floor beams are also prone to fatigue
cracking. Cracking of the frames was found on the fatigue test airplane
at about 40,000 total pressure cycles. As a result, we have determined
that additional inspections are necessary, as specified in the service
information described below.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 747-53A2349,
Revision 3, dated October 2, 2008 (``the service bulletin''). In AD
2005-20-30, we referred to Boeing Alert Service Bulletin 747-53A2349,
Revision 1, dated October 12, 2000; and Boeing Service Bulletin 747-
53A2349, Revision 2, dated April 3, 2003; as the appropriate sources of
service information for doing the actions required by that AD. Revision
3 of the service bulletin retains the procedures from Revision 2,
revises some airplane groups, and adds the repetitive inspections
listed in the table titled ``New Service Bulletin Procedures.''
[[Page 24713]]
New Service Bulletin Procedures
----------------------------------------------------------------------------------------------------------------
Revision 3 of the service bulletin adds procedures for
repetitive detailed inspections for cracking of these areas For airplanes identified as these groups in
specified in the service bulletin-- Revision 3 of the service bulletin--
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Additional inspections in Area 1: Fuselage frames at body 1 through 7 inclusive.
stations 260-520 in areas where the upper deck floor beams
are attached (Figure 11 of the Accomplishments
Instructions of the service bulletin).
Additional inspections in Area 6: Fuselage frames at body 6 and 7.
stations 400-500 in areas above the Main Entry Door 1
cutouts, from the upper chord of the upper deck floor
beams to Stringer 8 (Figure 12 of the Accomplishment
Instructions of the service bulletin).
----------------------------------------------------------------------------------------------------------------
The service bulletin specifies that the compliance time for the
inspections of additional areas is before 22,000 total flight cycles or
within 1,000 flight cycles after the date on the service bulletin,
whichever occurs later. The service bulletin also specifies repeating
the inspections at intervals not to exceed 3,000 flight cycles. The
service bulletin specifies to repair any crack or to contact Boeing for
repair instructions.
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 develop on other airplanes of the
same type design. For this reason, we are proposing this AD, which
would supersede AD 2005-20-30 and would retain the requirements of the
existing AD. This proposed AD would also require accomplishing the
additional actions specified in Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, described previously.
Change to Existing AD
This proposed AD would retain all requirements of AD 2005-20-30.
Since AD 2005-20-30 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
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2005-20-30 this proposed AD
------------------------------------------------------------------------
paragraph (f)............................. paragraph (g).
paragraph (g)............................. paragraph (h).
paragraph (h)............................. paragraph (i).
paragraph (i)............................. paragraph (j).
paragraph (j)............................. paragraph (k).
paragraph (k)............................. paragraph (l).
------------------------------------------------------------------------
Costs of Compliance
There are about 209 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. The average labor rate
is $80 per work hour.
Estimated Costs
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Cost per
Work airplane, per Number of U.S.-
Action hours inspection registered Fleet cost
cycle airplanes
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Inspections (required by AD 2005-20-30).............. 130 $10,400 69 $717,600
Additional inspections in Area 1 (new proposed 6 480 69 33,120
action).............................................
Additional inspections in Area 6 (new proposed 1 80 69 5,520
action).............................................
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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, Incorporation by
reference, 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:
[[Page 24714]]
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 removing amendment 39-14327 (70 FR
59252, October 12, 2005) and adding the following new AD:
Boeing: Docket No. FAA-2009-0477; Directorate Identifier 2008-NM-
191-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 10,
2009.
Affected ADs
(b) This AD supersedes AD 2005-20-30.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-100B
SUD, 747-200B, 747-300, 747SP, and 747SR series airplanes;
certificated in any category; identified in Boeing Service Bulletin
747-53A2349, Revision 3, dated October 2, 2008.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from fatigue tests and analysis by Boeing
that identified areas of the fuselage where fatigue cracks can
occur. We are issuing this AD to prevent the loss of the structural
integrity of the fuselage, which could result in rapid
depressurization of the airplane.
Compliance
(f) 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 Requirements of AD 2002-10-10
(Excluding Upper Deck Floor Beams)
Repetitive Inspections
(g) 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, which was superseded by AD 2002-
10-10), whichever occurs later, unless accomplished previously
within the last 2,000 flight cycles; and thereafter at intervals not
to exceed 3,000 flight cycles: Perform an internal detailed
inspection to detect cracks in the areas of the fuselage internal
structure specified in paragraphs (g)(1) through (g)(6) of this AD;
in accordance with Boeing Service Bulletin 747-53-2349, dated June
27, 1991; Boeing Alert Service Bulletin 747-53A2349, Revision 1,
dated October 12, 2000; Boeing Service Bulletin 747-53A2349,
Revision 2, dated April 3, 2003; or Boeing Alert Service Bulletin
747-53A2349, Revision 3, dated October 2, 2008. After the effective
date of this AD, only Revision 3 of Boeing Alert Service Bulletin
747-53A2349 may be used. Continue doing the inspections until the
inspections required by paragraph (j) of this AD are done.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Section 41 body station 260, 340, and 400 bulkheads.
(6) Main entry doors.
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
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(h) Prior to the accumulation of 25,000 total flight cycles, or
within 1,000 flight cycles after June 11, 1993, whichever is later,
unless already done within the last 2,000 flight cycles; and
thereafter at intervals not to exceed 3,000 flight cycles: Do an
internal detailed inspection to detect cracks in the Section 46
upper lobe frames, in accordance with Boeing Service Bulletin 747-
53-2349, dated June 27, 1991; Boeing Alert Service Bulletin 747-
53A2349, Revision 1, dated October 12, 2000; Boeing Service Bulletin
747-53A2349, Revision 2, dated April 3, 2003; or Boeing Alert
Service Bulletin 747-53A2349, Revision 3, dated October 2, 2008.
After the effective date of this AD, only Revision 3 of Boeing Alert
Service Bulletin 747-53A2349 may be used.
Repair of Cracks Detected During Paragraph (g) or (h) Inspections
(i) Before further flight, repair any cracks detected during the
inspections done per paragraph (g) or (h) of this AD by doing the
actions specified in paragraph (i)(1) or (i)(2) of this AD, as
applicable.
(1) Repair in accordance with a method approved by the Manager,
Seattle Aircraft Certification Office (ACO), FAA; or using a method
approved in accordance with paragraph (p) of this AD.
(2) Repair in accordance with Boeing Service Bulletin 747-
53A2349, Revision 2, dated April 3, 2003; or Boeing Alert Service
Bulletin 747-53A2349, Revision 3, dated October 2, 2008. After the
effective date of this AD, only Revision 3 of Boeing Alert Service
Bulletin 747-53A2349 may be used. Where either revision of the
service bulletin specifies to contact Boeing for repair
instructions, repair in accordance with a method approved by the
Manager, Seattle ACO; or using a method approved in accordance with
paragraph (p) of this AD.
Restatement of Requirements of AD 2005-20-30
Repetitive Inspections
(j) Do an internal detailed inspection to detect cracking in the
areas of the fuselage internal structure specified in paragraphs
(j)(1), (j)(2), and (j)(3) of this AD, and internal and external
detailed inspections of the areas specified in paragraphs (j)(4),
(j)(5), (j)(6), and (j)(7) of this AD. Do the inspections in
accordance with Boeing Service Bulletin 747-53A2349, Revision 2,
dated April 3, 2003; or Boeing Alert Service Bulletin 747-53A2349,
Revision 3, dated October 2, 2008. After the effective date of this
AD, only Revision 3 of Boeing Alert Service Bulletin 747-53A2349 may
be used. Do the inspections at the applicable time specified in
paragraph (k) of this AD. Accomplishment of these inspections
terminates the requirements of paragraph (g) of this AD.
(1) Section 42 upper lobe frames.
(2) Section 46 lower lobe frames.
(3) Section 42 lower lobe frames.
(4) Main entry door cutouts.
(5) Nose wheel well bulkheads, sidewall panels, and Station
(STA) 360 and 380 floor beams. These areas include Section 41 body
station 260, 340, and 400 bulkheads.
(6) Main entry doors.
(7) Main electronics bay access door cutout.
(k) Do the inspections required by paragraph (j) of this AD at
the applicable time specified in paragraph (k)(1), (k)(2), or (k)(3)
of this AD. Repeat the inspections thereafter at intervals not to
exceed 3,000 flight cycles.
(1) For airplanes on which the inspections required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD
have been done before November 16, 2005 (the effective date of AD
2005-20-30), but the inspections required by paragraphs (j)(5) and
(j)(7) of this AD have not been done: Within 3,000 flight cycles
since accomplishment of the most recent inspection required by
paragraphs (g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD,
except that the inspections specified in paragraphs (j)(5) and
(j)(7) of this AD may be done within 3,000 flight cycles since
accomplishment of the most recent inspection required by paragraphs
(g)(1), (g)(2), (g)(3), (g)(4), and (g)(6) of this AD, or within
1,000 flight cycles after November 16, 2005, whichever is later.
(2) For airplanes on which the inspections required by
paragraphs (j)(5) and (j)(7) have been done before November 16,
2005: Within 3,000 flight cycles since accomplishment of the most
recent inspection required by paragraphs (j)(5) and (j)(7) of this
AD, or within 1,000 flight cycles after November 16, 2005, whichever
is later.
(3) For airplanes on which the inspections required by paragraph
(g) of this AD have not been done before November 16, 2005: Prior to
the accumulation of 22,000 total flight cycles, or within 1,000
flight cycles after November 16, 2005, whichever is later.
Repair of Cracks Detected During Paragraph (j) Inspection
(l) Before further flight, repair any cracking found during any
inspection required by paragraph (j) of this AD in accordance with
Boeing Service Bulletin 747-53A2349, Revision 2, dated April 3,
2003; or Boeing Alert Service Bulletin 747-53A2349, Revision 3,
dated October 2, 2008. After the effective date of this AD, only
Revision 3 of Boeing Alert Service Bulletin 747-53A2349 may be used.
Where any revision of the service bulletin specifies to contact
Boeing for repair instructions, repair in accordance
[[Page 24715]]
with a method approved by the Manager, Seattle ACO; or using a
method approved in accordance with paragraph (p) of this AD.
New Requirements of This AD
Inspections and Repair
(m) Do initial and repetitive detailed inspections for cracking
in the areas specified in Table 1 of this AD using applicable
internal and external detailed inspection methods; and repair all
cracks, by doing all the applicable actions in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, except as required by
paragraph (n) of this AD. Do the initial and repetitive inspections
at the times specified in paragraph 1.E., ``Compliance,'' of the
service bulletin, except as required by paragraph (o) of this AD.
Repair all cracks before further flight after detection.
Table 1--Additional Inspections
------------------------------------------------------------------------
Inspect the addition portion of area 1 and area For airplanes
6 as specified in Boeing Alert Service Bulletin identified as these
747-53A2349, Revision 3, dated October 2, 2008 groups in the service
(``the service bulletin'')-- bulletin--
------------------------------------------------------------------------
In Area 1: Fuselage frames at body stations 260- 1 through 7 inclusive.
520 in areas where the upper deck floor beams
are attached (Figure 11 of the Accomplishments
Instructions of the service bulletin).
In Area 6: Fuselage frames at body stations 400- 6 and 7.
500 in areas above the Main Entry Door 1
cutouts, from the upper chord of the upper deck
floor beams to Stringer 8 (Figure 12 of the
Accomplishment Instructions of the service
bulletin).
------------------------------------------------------------------------
Exceptions to Certain Procedures
(n) If any crack is found during any inspection required by
paragraph (m) of this AD, and Boeing Alert Service Bulletin 747-
53A2349, Revision 3, dated October 2, 2008, specifies to contact
Boeing for appropriate action: Before further flight, repair the
crack using a method approved in accordance with the procedures
specified in paragraph (p) of this AD.
(o) Where Boeing Alert Service Bulletin 747-53A2349, Revision 3,
dated October 2, 2008, specifies a compliance time after the date on
Boeing Alert Service Bulletin 747-53A2349, Revision 3, dated October
2, 2008, this AD requires compliance within the specified compliance
time after the effective date of this AD.
Alternative Methods of Compliance (AMOCs)
(p)(1) The Manager, Seattle ACO, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to Attn: Ivan Li, Aerospace
Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 917-6437; fax (425) 917-6590. Or, e-mail
information to 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(3) AMOCs approved previously in accordance with AD 2005-20-30
are approved as AMOCs with the corresponding provisions of this AD.
(4) 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, and the approval must specifically refer to this
AD.
Issued in Renton, Washington, on May 15, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-12111 Filed 5-22-09; 8:45 am]
BILLING CODE 4910-13-P