[Federal Register Volume 75, Number 82 (Thursday, April 29, 2010)]
[Rules and Regulations]
[Pages 22514-22516]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-9091]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0381; Directorate Identifier 2009-NM-146-AD;
Amendment 39-16268; AD 2010-09-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-200B
Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
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SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Model 747-200B series airplanes. This AD requires repetitive
inspections for cracking of the fuselage skin lap joints at stringer 6
on the left and right sides from station (STA) 340 to STA 400, a one-
time general visual inspection to determine if certain fasteners are
installed and to determine if service repair manual (SRM) repairs or
repair doublers are installed, and corrective actions if necessary.
Doing an optional modification of the stringer 6 lap joints terminates
the repetitive inspections for the modified area. This AD results from
reviews done by Boeing, which show that airplanes that were modified by
Boeing to the stretched upper deck (SUD) configuration require
inspection for cracking of the stringer 6 lap joint upper-fastener row
earlier than previously expected. We are issuing this AD to detect and
correct cracking of the stringer 6 lap joints where certain external
doublers were not installed, which could result in rapid decompression
and loss of structural integrity of the airplane.
DATES: This AD is effective May 14, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of May 14, 2010.
We must receive comments on this AD by June 28, 2010.
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 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 [email protected]; Internet
https://www.myboeingfleet.com.
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 AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone 800-647-
[[Page 22515]]
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:
Discussion
Review by Boeing has determined that airplanes that were modified
by Boeing to the stretched upper deck (SUD) configuration require
inspecting the stringer 6 lap joint upper fastener row for cracking at
an earlier time than expected. Previously, no inspections of this area
were recommended prior to accomplishment of Boeing Service Bulletin
747-53-2272, Zone 1 modification, which involves installing external
doublers. If the external doublers have not been installed on the
stringer 6 lap joints, cracks could develop in the lap joints. Skin
cracks could join together and result in rapid decompression and loss
of structural integrity of the airplane.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 747-53A2809, dated June
18, 2009. This service bulletin specifies that, for airplanes with
external doublers installed in accordance with Boeing Service Bulletin
747-53-2272, no further work is necessary.
For the other affected airplanes, Boeing Alert Service Bulletin
747-53A2809, dated June 18, 2009, describes procedures for repetitive
external detailed and high frequency eddy current (HFEC) inspections to
detect cracking of the left and right side stringer 6 lap joints, doing
a one-time general visual inspection to determine whether certain
fasteners exist in the upper-fastener row of the lap joints and to
determine whether any service repair manual (SRM) repairs or repair
doublers are installed, and corrective actions if necessary. Corrective
actions include repairing any cracks that are found, and contacting
Boeing for repair instructions if certain fasteners, or if any SRM
repairs or repair doublers other than those installed per Boeing
Service Bulletin 747-53-2272,
Zone 1 modification, are found in the inspection area.
Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009,
also specifies that the optional accomplishment of a modification would
eliminate the need to do the repetitive inspections, repair cracks, or
contact Boeing for instructions if certain fasteners are found. This
modification involves removing the upper row of fasteners at the
stringer 6 lap joints from STA 340 to STA 400 doing open-hole HFEC
inspections to detect skin cracks; and doing corrective actions if
necessary (e.g., trimming out any cracks found during any inspection),
and installing external doublers as specified in the Zone 1
modification of Boeing Service Bulletin 747-53-2272.
The compliance time for the initial inspections is 10,000 flight
cycles after the airplane was modified to the SUD configuration, or
within 50 flight cycles after the date on Boeing Alert Service Bulletin
747-53A2809, whichever occurs later. The repetitive interval is 3,000
flight cycles. The compliance time for the corrective actions is before
further flight.
FAA's Determination and Requirements of This AD
No Model 747-200B series airplanes affected by this AD are on the
U.S. Register. We are issuing this AD because the unsafe condition
described previously is likely to exist or develop on other products of
the same type design that could be registered in the United States in
the future. This AD requires repetitive inspections of the left and
right side stringer 6 lap joints from STA 340 to STA 400.
Since no U.S. Model 747-200B series airplanes are affected by this
AD, notice and opportunity for public comment before issuing this AD
are unnecessary.
Differences Between the AD and the Service Information
Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009,
specifies to contact the manufacturer for instructions on how to repair
certain conditions, but this 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 (ODA) that has been
authorized by the Manager, Seattle ACO, to make those findings.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2010-0381; Directorate Identifier 2009-NM-146-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this 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 AD.
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
This AD will not have federalism implications under Executive Order
13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD docket.
[[Page 22516]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2010-09-03 The Boeing Company: Amendment 39-16268. Docket No. FAA-
2010-0381; Directorate Identifier 2009-NM-146-AD.
Effective Date
(a) This airworthiness directive (AD) is effective May 14, 2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to The Boeing Company Model 747-200B series
airplanes, certificated in any category, identified as Group 1,
Configuration 2, in Boeing Alert Service Bulletin 747-53A2809, dated
June 18, 2009.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from reviews done by Boeing, which show that
airplanes modified to the stretched upper deck (SUD) configuration
by Boeing require inspection for cracking of the upper-fastener row
of the left and right side stringer 6 lap joints earlier than
expected. The Federal Aviation Administration is issuing this AD to
detect and correct cracking of the stringer 6 lap joints where
certain external doublers were not installed, which could result in
rapid decompression and loss of structural integrity 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.
Inspections
(g) Except as required by paragraphs (h) and (i) of this AD: At
the applicable time specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2809, dated June 18, 2009, do
the inspections specified in paragraphs (g)(1) and (g)(2) of this
AD, and applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2809, dated June 18, 2009. Do all applicable corrective actions
before further flight. Repeat the inspections specified in paragraph
(g)(1) of this AD thereafter at intervals not to exceed 3,000 flight
cycles, except as provided by paragraph (j) of this AD.
(1) Inspect the left and right side stringer 6 lap joints from
station (STA) 340 to STA 400. The inspections include external
detailed and high frequency eddy current (HFEC) inspections for
cracks in the skin in areas that have not been modified or repaired
as specified in paragraph 3.B., Part 2 or Part 3, respectively, of
the Accomplishment Instructions of Boeing Alert Service Bulletin
747-53A2809, dated June 18, 2009.
(2) Do a one-time general visual inspection of the lap joints to
determine if certain fasteners are installed and to determine if
structural repair manual (SRM) repairs or repair doublers are
installed.
Note 1: For airplanes on which external doublers have been
installed on both side of the airplanes in accordance with Boeing
Service Bulletin 747-53-2272, Zone 1 modification, no further work
is necessary.
Exceptions to Service Bulletin
(h) Where Boeing Alert Service Bulletin 747-53A2809, dated June
18, 2009, specifies a compliance time after the date on that service
bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
(i) For any condition in which Boeing Alert Service Bulletin
747-53A2809, dated June 18, 2009, specifies to contact Boeing for
appropriate action: those actions must be approved using a method
approved in accordance with the procedures specified in paragraph
(k) of this AD.
Optional Terminating Action
(j) Accomplishing the modification, including the open-hole HFEC
inspections to detect skin cracks, and applicable corrective
actions, specified in paragraph 3.B., Part 2, of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-53A2809, dated
June 18, 2009, terminates the repetitive inspections and repair
requirements specified in paragraph (g) of this AD for the side of
the airplane on which the modification is done.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (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 ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
telephone (425) 917-6437; fax (425) 917-6590. Or, e-mail information
to [email protected].
(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.
Material Incorporated by Reference
(l) You must use Boeing Alert Service Bulletin 747-53A2809,
dated June 18, 2009, to do the actions required by this AD, unless
the AD specifies otherwise. If you accomplish the optional
terminating actions specified by this AD, you must use Boeing Alert
Service Bulletin 747-53A2809, dated June 18, 2009, as applicable, to
perform those actions, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this 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
[email protected]; Internet https://www.myboeingfleet.com.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 9, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service..
[FR Doc. 2010-9091 Filed 4-28-10; 8:45 am]
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