Airworthiness Directives; The Boeing Company Model 747-100, -200B, and -200F Series Airplanes, 8554-8557 [2010-3819]
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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules
TABLE 1—AFFECTED CHECK VALVE INSTALLATION—Continued
Affected check valve installation, identified by FIN
(functional item number)
Compliance time
(iii) Airplanes having Hydraulic System with FIN 29/1378, FIN 29/1382
and FIN 29/1394.
(iv) Hydraulic System (A300 airplanes having configuration 01
‘‘pre-Airbus modification 03079’’ only) FIN 29/1381.
(2) Check valves P/N 2S2794–1 marked
with an ‘‘R’’ have already been modified in
accordance with Crissair Service Bulletin
20070407–29–1 and do not need to be
Within 30 months after the effective date of this AD.
Within 30 months after the effective date of this AD.
replaced. Check valves with P/N 2S2794 are
not affected and do not need to be replaced.
(3) As of the effective date of this AD, no
person may install any Crissair check valve,
P/N 2S2794–1, on any airplane unless it has
a serial number other than those listed in
Appendix 1 of the applicable service bulletin
identified in Table 2 of this AD, or unless
check valve P/N 2S2794–1 is marked with an
‘‘R.’’
TABLE 2—SERVICE INFORMATION
Airbus model—
Airbus Mandatory Service Bulletin—
A300 airplanes .............................
A300–600 airplanes .....................
A310 airplanes .............................
A300–29–0124, including Appendices 1, 2, and 3 ...........................
A300–29–6060, including Appendices 1, 2, and 3 ...........................
A310–29–2097, including Appendices 1, 2, and 3 ...........................
(4) Submit an inspection report of the
inspection required by paragraph (f)(1) of this
AD to Airbus Customer Services Directorate,
1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61
93 33 33; fax +33 5 61 93 42 51; e-mail:
sb.reporting@airbus.com; at the applicable
time specified in paragraph (f)(4)(i) or
(f)(4)(ii) of this AD. The report must include
the information specified on the inspection
report sheet provided in the applicable
service bulletin identified in Table 2 of this
AD.
(i) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
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FAA AD Differences
Note 1: This AD differs from the MCAI
and/or service information as follows:
Although the MCAI states not to install the
part identified in paragraph (f)(3) of this AD
after accomplishing the actions specified in
paragraph (f)(1) of this AD, this AD prohibits
installation of the part as of the effective date
of this AD.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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: Dan Rodina,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–2125; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
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17:18 Feb 24, 2010
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Revision—
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.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the Information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI EASA Airworthiness
Directive 2009–0171, dated August 5, 2009;
and the service bulletins identified in Table
2 of this AD; for related information.
Issued in Renton, Washington, on February
17, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3817 Filed 2–24–10; 8:45 am]
BILLING CODE 4910–13–P
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Dated—
02
01
01
March 10, 2009.
March 10, 2009.
March 19, 2009.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0132; Directorate
Identifier 2009–NM–096–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–100, –200B, and
–200F 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
Model 747–100, 747–200B, and –200F
series airplanes. The existing AD
currently requires inspections to detect
cracking in the upper row of fasteners
holes of the skin lap joints in the
fuselage lower lobe, and repair, if
necessary. This proposed AD would
reduce the maximum interval of the
post-modification inspections. This
proposed AD results from reports of
fatigue cracking on modified airplanes.
We are proposing this AD to detect and
correct fatigue cracking in the
longitudinal lap joints of the fuselage
lower lobe, which could lead to the
rapid decompression of the airplane and
the inability of the structure to carry
fail-safe loads.
DATES: We must receive comments on
this proposed AD by April 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules
• Federal eRulemaking Portal: Go to
https://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 https://
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:
sroberts on DSKD5P82C1PROD with PROPOSALS
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–2010–0132; Directorate Identifier
2009–NM–096–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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19:28 Feb 24, 2010
Jkt 220001
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 https://
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 August 4, 1994, we issued AD 94–
17–01, Amendment 39–8996 (59 FR
41653, August 15, 1994), for certain
Model 747 series airplanes. That AD
requires inspections to detect cracking
in the upper row of fastener holes of the
skin lap joints in the fuselage lower
lobe, and repair if necessary. That AD
resulted from reports of incidents
involving fatigue cracking and corrosion
of transport category airplanes that are
approaching or have exceeded their
design life goal. We issued that AD to
prevent separation of fuselage skin and
rapid loss of pressure in the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 94–17–01, Boeing
has performed a fleet-wide evaluation of
the skin panel lap joints for widespread
fatigue damage (WFD) and determined
that the post-modification inspection
interval of AD 94–17–01 needs to be
reduced. In addition, lap joints where
the upper (overlapping) skin thickness
at the upper row of fasteners is 0.071
inch or less need to be further modified
to preclude WFD. WFD of the lap joints
can link up and result in large skin
cracks, and possible rapid in-flight
decompression of the airplane.
Relevant Service Information
AD 94–17–01 referred to Boeing
Service Bulletin 747–53A2267, Revision
3, dated March 26, 1992, as the
appropriate source of service
information. Boeing has since issued
Alert Service Bulletin 747–53A2267,
Revision 4, dated March 26, 2009. This
service bulletin reduces the repetitive
interval for the post-modification
inspections and references a structural
modification for lap joints where the
upper (overlapping) skin thickness at
the upper row of fasteners is 0.071 inch
or less.
Related Rulemaking
We are considering issuing related
rulemaking to address the identified
unsafe condition. We are in the process
of issuing an AD that will refer to
Revision 1 of Boeing Alert Service
Bulletin 747–53A2463, and is related to
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8555
this issue. That AD will require further
modification of all the affected lap joints
with an upper skin thickness of 0.071
inch or less.
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 94–17–
01. This AD would retain the
requirements of that AD using the
revised service information, and reduce
the maximum interval of the postmodification inspections from 3,000
flight cycles to 1,000 flight cycles.
Differences Between the Proposed AD
and Service Bulletin
Boeing Alert Service Bulletin 747–
53A2267, Revision 4, dated March 26,
2009, 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 the Boeing
Commercial Airplanes Organization
Designation Authorization that we have
authorized to make those findings.
Changes to Existing AD
This proposed AD would retain the
requirements of AD 94–17–01. Since AD
94–17–01 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
Requirement in
AD 94–17–01
Corresponding
requirement in this
proposed AD
Paragraph (a)
Paragraph (b)
Paragraph (c)
Paragraph (g).
Paragraph (h).
Paragraph (i).
This proposed AD identifies the legal
name of the manufacturer as published
in the most recent type certificate data
sheet for the affected airplane models.
Costs of Compliance
There are about 23 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.
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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules
ESTIMATED COSTS
Action
Work hours
Inspection (required by AD
94–17–01).
Average
labor rate
per hour
244
Parts
$85
$0
$20,740 per inspection
cycle.
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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.
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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
removing Amendment 39–8996 (59 FR
41653, August 15, 1994) and adding the
following new AD:
The Boeing Company: Docket No. FAA–
2010–0132; Directorate Identifier 2009–
NM–096–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by April 12, 2010.
Affected ADs
(b) This AD supersedes AD 94–17–01,
Amendment 39–8996.
Applicability
(c) This AD applies to The Boeing
Company Model 747–100, 747–200B, and
747–200F series airplanes, certificated in any
category, as identified in Boeing Alert
Service Bulletin 747–53A2267, Revision 4,
dated March 26, 2009.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from reports of fatigue
cracking. The Federal Aviation
Administration is issuing this AD to detect
and correct fatigue cracking in the fuselage
lower lobe longitudinal lap joints, which
could lead to the rapid decompression of the
airplane and the inability of the structure to
carry fail-safe loads.
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.
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Number of
U.S.
-registered
airplanes
Cost per airplane
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7
Fleet cost
$145,180 per inspection
cycle.
Restatement of Requirements of AD 94–17–
01, with Revised Compliance Times for PostModification Inspection and Revised Service
Information:
Initial External High Frequency Eddy
Current Inspection
(g) Perform an external high frequency
eddy current inspection to detect cracks in
the upper row of fasteners in the modified
lap joints in accordance with Boeing Service
Bulletin 747–53A2267, Revision 3, dated
March 26, 1992; or Revision 4, dated March
26, 2009; at the time specified in paragraph
(g)(1) or (g)(2) or (g)(3) of this AD, as
applicable. As of the effective date of this
AD, only Revision 4 may be used.
(1) For airplanes on which the full
modification required by AD 90–06–06,
Amendment 39–6490, has been
accomplished in accordance with Revision 2
of Boeing Service Bulletin 747–53A2267,
dated March 29, 1990; or Revision 3, dated
March 26, 1992; or Revision 4, dated March
26, 2009: Prior to the accumulation of 10,000
flight cycles after accomplishment of the full
modification.
(2) For airplanes on which the full
modification required by AD 90–06–06 has
been accomplished in accordance with
Boeing Service Bulletin 747–53A2267, dated
March 28, 1986; or Revision 1, dated
September 25, 1986: Prior to the
accumulation of 7,000 flight cycles after
accomplishment of the full modification.
(3) For airplanes on which the optional
modification has been accomplished in
accordance with Boeing Service Bulletin
747–53A2267, Revision 2, dated March 29,
1990; or Revision 3, dated March 26, 1992;
or Revision 4, dated March 26, 2009: Prior to
the accumulation of 7,000 flight cycles after
accomplishment of the optional
modification.
Repetitive External High Frequency Eddy
Current Inspections
(h) If no cracking is detected during the
inspection required by paragraph (g) of this
AD, repeat the inspection required by
paragraph (g) of this AD at the earlier of the
times specified in paragraphs (h)(1) and
(h)(2) of this AD, and thereafter at intervals
not to exceed 1,000 flight cycles.
(1) Within 3,000 flight cycles after the last
inspection required by paragraph (g) of this
AD.
(2) Within 1,000 flight cycles after the last
inspection required by paragraph (g) of this
AD or 500 flight cycles after the effective date
of this AD, whichever occurs later.
Repair
(i) If any cracking is detected during any
inspection required by paragraph (g) of this
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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Proposed Rules
AD, prior to further flight, repair in
accordance with Section 53–30–03 of the
Boeing 747 Structural Repair Manual (SRM);
or Boeing Alert Service Bulletin 747–
53A2267, Revision 4, dated March 26, 2009;
except as required by paragraph (j) of this
AD; and repeat the inspection required by
paragraph (g) of this AD at the times
specified in paragraph (i)(1) of this AD. After
the effective date of this AD, use only Boeing
Alert Service Bulletin 747–53A2267,
Revision 4, dated March 26, 2009.
(1) As of the effective date of this AD: If
the repair specified in the Boeing 747 SRM
does not include removing the lap joint and
the upper row of countersunk fasteners,
repeat the inspection required by paragraph
(g) of this AD at the earlier of the times
specified in paragraphs (i)(1)(i) and (i)(1)(ii)
of this AD, and thereafter at intervals not to
exceed 1,000 flight cycles.
(i) Within 3,000 flight cycles after the last
inspection required by paragraph (g) of this
AD.
(ii) Within 1,000 flight cycles after the last
inspection required by paragraph (g) of this
AD, or within 500 flight cycles after the
effective date of this AD, whichever occurs
later.
(2) If the repair specified in the 747 SRM
includes removing the lap joint and the
upper row of countersunk fasteners, such
repair constitutes terminating action for the
inspection requirements of this AD.
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Exception to the Service Bulletin
(j) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2267,
Revision 4, dated March 26, 2009, specifies
contacting Boeing for appropriate action:
Before further flight, repair the cracking
using a method approved in accordance with
the procedures specified in paragraph (k) of
this AD. For a repair method to be approved
by the Manager, Seattle ACO, as required by
this paragraph, the Manager’s approval letter
must specifically refer to this AD.
Alternative Methods of Compliance
(AMOCs)
(k)(1) The Manager, Seattle Aircraft
Certification Office, 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-AMOCRequests@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) An AMOC that provides an acceptable
level of safety may be used for any repair
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17:18 Feb 24, 2010
Jkt 220001
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that 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) AMOCs approved previously in
accordance with AD 94–17–01 are approved
as AMOCs for the corresponding provisions
of this AD.
Issued in Renton, Washington, on February
17, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3819 Filed 2–24–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0170; Directorate
Identifier 2009–NM–127–AD]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model EMB–135ER,
–135KE, –135KL, and –135LR
Airplanes; and EMBRAER Model EMB–
145, –145ER, –145MR, –145LR,
–145XR, –145MP, and –145EP
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
Reassessment of the damage tolerance
analysis resulted in threshold reduction for
some Structure Significant Items (SSI) of the
Maintenance Review Board Report (MRBR)
Airworthiness Limitations Items (ALI).
Failure to inspect these structural
components, according to the new threshold,
could prevent a timely detection of fatigue
cracking. These cracks, if not properly
addressed, could adversely affect the
structural integrity of the airplane.
*
*
*
*
*
The proposed AD would require
actions that are intended to address the
unsafe condition described in the MCAI.
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8557
DATES: We must receive comments on
this proposed AD by April 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://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 W12–40, 1200 New Jersey
Avenue, SE., 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 Empresa
Brasileira de Aeronautica S.A.
(EMBRAER), Technical Publications
Section (PC 060), Av. Brigadeiro Faria
˜
Lima, 2170—Putim—12227–901 Sao
Jose dos Campos—SP—BRASIL;
telephone: +55 12 3927–5852 or +55 12
3309–0732; fax: +55 12 3927–7546;
e-mail: distrib@embraer.com.br;
Internet: https://www.flyembraer.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 https://
www.regulations.gov; or in person at the
Docket Operations office 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 Operations
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:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
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
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[Federal Register Volume 75, Number 37 (Thursday, February 25, 2010)]
[Proposed Rules]
[Pages 8554-8557]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3819]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0132; Directorate Identifier 2009-NM-096-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-100, -
200B, and -200F 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 Model 747-100, 747-200B, and -
200F series airplanes. The existing AD currently requires inspections
to detect cracking in the upper row of fasteners holes of the skin lap
joints in the fuselage lower lobe, and repair, if necessary. This
proposed AD would reduce the maximum interval of the post-modification
inspections. This proposed AD results from reports of fatigue cracking
on modified airplanes. We are proposing this AD to detect and correct
fatigue cracking in the longitudinal lap joints of the fuselage lower
lobe, which could lead to the rapid decompression of the airplane and
the inability of the structure to carry fail-safe loads.
DATES: We must receive comments on this proposed AD by April 12, 2010.
ADDRESSES: You may send comments by any of the following methods:
[[Page 8555]]
Federal eRulemaking Portal: Go to https://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 https://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-2010-0132;
Directorate Identifier 2009-NM-096-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 https://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 August 4, 1994, we issued AD 94-17-01, Amendment 39-8996 (59 FR
41653, August 15, 1994), for certain Model 747 series airplanes. That
AD requires inspections to detect cracking in the upper row of fastener
holes of the skin lap joints in the fuselage lower lobe, and repair if
necessary. That AD resulted from reports of incidents involving fatigue
cracking and corrosion of transport category airplanes that are
approaching or have exceeded their design life goal. We issued that AD
to prevent separation of fuselage skin and rapid loss of pressure in
the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 94-17-01, Boeing has performed a fleet-wide
evaluation of the skin panel lap joints for widespread fatigue damage
(WFD) and determined that the post-modification inspection interval of
AD 94-17-01 needs to be reduced. In addition, lap joints where the
upper (overlapping) skin thickness at the upper row of fasteners is
0.071 inch or less need to be further modified to preclude WFD. WFD of
the lap joints can link up and result in large skin cracks, and
possible rapid in-flight decompression of the airplane.
Relevant Service Information
AD 94-17-01 referred to Boeing Service Bulletin 747-53A2267,
Revision 3, dated March 26, 1992, as the appropriate source of service
information. Boeing has since issued Alert Service Bulletin 747-
53A2267, Revision 4, dated March 26, 2009. This service bulletin
reduces the repetitive interval for the post-modification inspections
and references a structural modification for lap joints where the upper
(overlapping) skin thickness at the upper row of fasteners is 0.071
inch or less.
Related Rulemaking
We are considering issuing related rulemaking to address the
identified unsafe condition. We are in the process of issuing an AD
that will refer to Revision 1 of Boeing Alert Service Bulletin 747-
53A2463, and is related to this issue. That AD will require further
modification of all the affected lap joints with an upper skin
thickness of 0.071 inch or less.
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 94-17-01. This AD would retain the requirements of
that AD using the revised service information, and reduce the maximum
interval of the post-modification inspections from 3,000 flight cycles
to 1,000 flight cycles.
Differences Between the Proposed AD and Service Bulletin
Boeing Alert Service Bulletin 747-53A2267, Revision 4, dated March
26, 2009, 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 the Boeing Commercial
Airplanes Organization Designation Authorization that we have
authorized to make those findings.
Changes to Existing AD
This proposed AD would retain the requirements of AD 94-17-01.
Since AD 94-17-01 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 in this
Requirement in AD 94-17-01 proposed AD
------------------------------------------------------------------------
Paragraph (a) Paragraph (g).
Paragraph (b) Paragraph (h).
Paragraph (c) Paragraph (i).
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This proposed AD identifies the legal name of the manufacturer as
published in the most recent type certificate data sheet for the
affected airplane models.
Costs of Compliance
There are about 23 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.
[[Page 8556]]
Estimated Costs
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Number of
Average U.S. -
Action Work hours labor rate Parts Cost per airplane registered Fleet cost
per hour airplanes
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Inspection (required by AD 94-17-01) 244 $85 $0 $20,740 per inspection 7 $145,180 per inspection cycle.
cycle.
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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:
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 39-8996 (59 FR
41653, August 15, 1994) and adding the following new AD:
The Boeing Company: Docket No. FAA-2010-0132; Directorate Identifier
2009-NM-096-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by April 12,
2010.
Affected ADs
(b) This AD supersedes AD 94-17-01, Amendment 39-8996.
Applicability
(c) This AD applies to The Boeing Company Model 747-100, 747-
200B, and 747-200F series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 747-53A2267, Revision
4, dated March 26, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reports of fatigue cracking. The
Federal Aviation Administration is issuing this AD to detect and
correct fatigue cracking in the fuselage lower lobe longitudinal lap
joints, which could lead to the rapid decompression of the airplane
and the inability of the structure to carry fail-safe loads.
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 94-17-01, with Revised
Compliance Times for Post-Modification Inspection and Revised
Service Information:
Initial External High Frequency Eddy Current Inspection
(g) Perform an external high frequency eddy current inspection
to detect cracks in the upper row of fasteners in the modified lap
joints in accordance with Boeing Service Bulletin 747-53A2267,
Revision 3, dated March 26, 1992; or Revision 4, dated March 26,
2009; at the time specified in paragraph (g)(1) or (g)(2) or (g)(3)
of this AD, as applicable. As of the effective date of this AD, only
Revision 4 may be used.
(1) For airplanes on which the full modification required by AD
90-06-06, Amendment 39-6490, has been accomplished in accordance
with Revision 2 of Boeing Service Bulletin 747-53A2267, dated March
29, 1990; or Revision 3, dated March 26, 1992; or Revision 4, dated
March 26, 2009: Prior to the accumulation of 10,000 flight cycles
after accomplishment of the full modification.
(2) For airplanes on which the full modification required by AD
90-06-06 has been accomplished in accordance with Boeing Service
Bulletin 747-53A2267, dated March 28, 1986; or Revision 1, dated
September 25, 1986: Prior to the accumulation of 7,000 flight cycles
after accomplishment of the full modification.
(3) For airplanes on which the optional modification has been
accomplished in accordance with Boeing Service Bulletin 747-53A2267,
Revision 2, dated March 29, 1990; or Revision 3, dated March 26,
1992; or Revision 4, dated March 26, 2009: Prior to the accumulation
of 7,000 flight cycles after accomplishment of the optional
modification.
Repetitive External High Frequency Eddy Current Inspections
(h) If no cracking is detected during the inspection required by
paragraph (g) of this AD, repeat the inspection required by
paragraph (g) of this AD at the earlier of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, and thereafter at intervals
not to exceed 1,000 flight cycles.
(1) Within 3,000 flight cycles after the last inspection
required by paragraph (g) of this AD.
(2) Within 1,000 flight cycles after the last inspection
required by paragraph (g) of this AD or 500 flight cycles after the
effective date of this AD, whichever occurs later.
Repair
(i) If any cracking is detected during any inspection required
by paragraph (g) of this
[[Page 8557]]
AD, prior to further flight, repair in accordance with Section 53-
30-03 of the Boeing 747 Structural Repair Manual (SRM); or Boeing
Alert Service Bulletin 747-53A2267, Revision 4, dated March 26,
2009; except as required by paragraph (j) of this AD; and repeat the
inspection required by paragraph (g) of this AD at the times
specified in paragraph (i)(1) of this AD. After the effective date
of this AD, use only Boeing Alert Service Bulletin 747-53A2267,
Revision 4, dated March 26, 2009.
(1) As of the effective date of this AD: If the repair specified
in the Boeing 747 SRM does not include removing the lap joint and
the upper row of countersunk fasteners, repeat the inspection
required by paragraph (g) of this AD at the earlier of the times
specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD, and
thereafter at intervals not to exceed 1,000 flight cycles.
(i) Within 3,000 flight cycles after the last inspection
required by paragraph (g) of this AD.
(ii) Within 1,000 flight cycles after the last inspection
required by paragraph (g) of this AD, or within 500 flight cycles
after the effective date of this AD, whichever occurs later.
(2) If the repair specified in the 747 SRM includes removing the
lap joint and the upper row of countersunk fasteners, such repair
constitutes terminating action for the inspection requirements of
this AD.
Exception to the Service Bulletin
(j) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2267, Revision 4,
dated March 26, 2009, specifies contacting Boeing for appropriate
action: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD. For a repair method to be approved by the Manager,
Seattle ACO, as required by this paragraph, the Manager's approval
letter must specifically refer to this AD.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office, 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) An AMOC that provides an acceptable level of safety may be
used for any repair required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that 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) AMOCs approved previously in accordance with AD 94-17-01 are
approved as AMOCs for the corresponding provisions of this AD.
Issued in Renton, Washington, on February 17, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3819 Filed 2-24-10; 8:45 am]
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