[Federal Register: December 11, 2008 (Volume 73, Number 239)]
[Rules and Regulations]
[Page 75305-75307]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11de08-1]
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Rules and Regulations
Federal Register
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[[Page 75305]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0590; Directorate Identifier 2008-NM-057-AD;
Amendment 39-15765; AD 2008-25-07]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for all
Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-
200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes.
This AD requires repetitive inspections for cracks or fractures of the
forward end attachment and the forward lower flange of the flap tracks
of the trailing edge flaps, and corrective actions if necessary. For
certain airplanes, this AD would also require modifying the fail-safe
links of the main carriage. This AD results from a detailed structural
analysis of the flap attach structural and fail-safe components,
accomplished as a result of a dynamic stability and control analysis,
which could not demonstrate continued safe flight and landing of the
airplane after the loss of a trailing edge flap. We are issuing this AD
to detect and correct cracks or fractures of the primary structural and
fail-safe load paths of the inboard and outboard trailing edge flaps,
which could result in the loss of a flap during takeoff or landing,
reducing flightcrew ability to maintain the safe flight and landing of
the airplane.
DATES: This AD is effective January 15, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 15,
2009.
ADDRESSES: 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 me.boecom@boeing.com;
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 address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Oltman, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6443; fax (425) 917-6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that would apply to
all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C,
747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series
airplanes. That NPRM was published in the Federal Register on May 23,
2008 (73 FR 30003) That NPRM proposed to require repetitive inspections
for cracks or fractures of the forward end attachment and the forward
lower flange of the flap tracks of the trailing edge flaps, and
corrective actions if necessary. For certain airplanes, that NPRM would
also require modifying the fail-safe links of the main carriage.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comments received from the commenters.
Support for the NPRM
Boeing has reviewed the NPRM and concurs with the content of the
proposed rule.
Request To Extend Certain Compliance Times
Northwest Airlines (NWA) asks that the repetitive inspection
intervals for the Part 1 inspections, as required by paragraph (f) of
the NPRM, be changed to specify intervals not to exceed 750 flight
cycles after accomplishing the last inspection or within 750 flight
cycles after the flap track overhaul, whichever occurs later. For Part
3 inspections, NWA asks that the repetitive inspection interval be
changed to intervals not to exceed 1,500 flight cycles after
accomplishing the last inspection or within 1,500 flight cycles after
flap track overhaul, whichever occurs later. NWA adds that the reason
for the request is that, as part of its procedure for removing the
track for overhaul, the attaching fuse pin is removed and inspected and
the defined support fitting is inspected for condition; any failure of
the track would be detected during the track overhaul.
We do not agree with NWA's request to change the repetitive
inspection interval. The structural analysis of the flap attach
structural and fail-safe components supports the compliance time
specified for the repetitive inspection interval. In developing an
appropriate compliance time for this action, we considered the urgency
associated with the subject unsafe condition and the practical aspect
of accomplishing the required inspections within a period of time that
corresponds to the normal scheduled maintenance for most affected
operators. These maintenance schedules can vary greatly from operator
to operator. In light of these items, we have determined that the
repetitive inspection intervals specified in the service bulletin are
appropriate. However, according to the provisions of paragraph (j) of
this AD, we may approve requests to adjust the compliance time if the
request includes data that prove that the new compliance time would
provide an acceptable level
[[Page 75306]]
of safety. We have not changed the AD in this regard.
NWA also asks that the FAA review the 750-flight-cycle repetitive
inspection interval requirement, and if supported by new analysis,
change it to 1,000 flight cycles. NWA states that a 1,000-flight-cycle
interval would permit accomplishing the inspections in conjunction with
scheduled airplane maintenance.
We do not agree with the request to change the interval for the
repetitive inspections to 1,000 flight cycles. Previous analysis
supports the current 750-flight-cycle interval, and no new analysis is
currently available. However, as noted in the response to the previous
comment, we will consider requests for approval of an AMOC if
sufficient data are submitted that the new compliance time would
provide an acceptable level of safety. We have not changed the AD in
this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD as proposed.
Costs of Compliance
We estimate that this AD affects 190 airplanes of U.S. registry.
The following table provides the estimated costs for U.S. operators to
comply with this AD.
Estimated Costs
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Number of
Average U.S.-
Action Work hours labor rate Parts Cost per product registered Fleet cost
per hour airplanes
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Part 1 Inspections................ 4.................... $80 $0................... $320 per inspection 190 $60,800 per
cycle. inspection cycle.
Part 3 Inspections................ 4.................... 80 $0................... $320 per inspection 190 $60,800 per
cycle. inspection cycle.
Part 2 Modification for Groups 1-3 Between 3 and 7...... 80 Between $212 and Between $452 and 182 Between $82,264 and
Airplanes. $7,934. $8,494. $1,545,908.
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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
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.
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:
2008-25-07 Boeing: Amendment 39-15765. Docket No. FAA-2008-0590;
Directorate Identifier 2008-NM-057-AD.
Effective Date
(a) This airworthiness directive (AD) is effective January 15,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model 747-100, 747-100B, 747-
100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D,
747-400F, and 747SR series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a detailed structural analysis of the
flap attach structural and fail-safe components accomplished as a
result of a dynamic stability and control analysis, which could not
demonstrate continued safe flight and landing of the airplane after
the loss of a trailing edge flap. We are issuing this AD to detect
and correct cracks or fractures of the primary structural and fail-
safe load paths of the inboard and outboard trailing edge flaps,
which could result in the loss of a flap during takeoff or landing,
reducing flightcrew ability to maintain the safe flight and landing
of the airplane.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
Repetitive Inspections/Corrective Actions
(f) For all airplanes: Except as provided by paragraph (h) of
this AD, at the applicable times specified in paragraph 1.E. of
Boeing Alert Service Bulletin 747-57A2323, dated February 21, 2008,
inspect for cracks or fractures of the forward end attachment and
the forward lower flange of the flap tracks of the trailing edge
flaps, and do all applicable corrective actions, by doing all the
actions specified in Parts 1 and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2323, dated
[[Page 75307]]
February 21, 2008, except as provided by paragraph (i) of this AD.
Do all applicable corrective actions before further flight. Repeat
the applicable inspection at the applicable time specified in
paragraph 1.E. of Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008.
Modification of Fail Safe Links of Main Carriage
(g) For Groups 1, 2, and 3 airplanes: Within 24 months after the
effective date of this AD, replace the fail-safe links, pins, and
attachment hardware in accordance with Part 2 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008.
Exception to Compliance Times
(h) Where Boeing Alert Service Bulletin 747-57A2323, dated
February 21, 2008, specifies counting the compliance time from ``* *
* the date on this service bulletin,'' this AD requires counting the
compliance time from the effective date of this AD.
Exception to Corrective Actions
(i) If any fractured support fitting is found during any
inspection required by this AD, and Boeing Alert Service Bulletin
747-57A2323, dated February 21, 2008, specifies to contact Boeing
for appropriate action: Before further flight, repair using a method
approved in accordance with the procedures specified in paragraph
(j) of this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, ATTN: Gary Oltman, Aerospace Engineer, Airframe Branch, ANM-
120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356;
telephone (425) 917-6443; fax (425) 917-6590; has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19.
(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 appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(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, and the approval must specifically refer to this
AD.
Material Incorporated by Reference
(k) You must use Boeing Alert Service Bulletin 747-57A2323,
dated February 21, 2008; to do the actions required by this AD,
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
me.boecom@boeing.com; Internet https://www.myboeingfleet.com.
(3) You may review copies of the service information that is
incorporated by reference 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.
(4) You may also review copies of the service information 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 November 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-29073 Filed 12-10-08; 8:45 am]
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