[Federal Register: February 26, 2009 (Volume 74, Number 37)]
[Rules and Regulations]
[Page 8737-8739]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26fe09-14]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1006; Directorate Identifier 2008-NM-110-AD;
Amendment 39-15822; AD 2009-04-16]
RIN 2120-AA64
Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-
200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Boeing Model 747-100, 747-100B, 747-
200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes.
That AD currently requires an inspection to determine if acceptable
external skin doublers are installed at the stringer 6 (S-6) lap
splices, between station (STA) 340 and STA 400. For airplanes without
the acceptable external skin doublers, the existing AD also requires
repetitive related investigative actions and corrective actions if
necessary. The existing AD also provides an optional terminating
modification for the repetitive related investigative actions. This new
AD mandates the optional terminating modification. This AD results from
a report of cracked fastener holes at the right S-6 lap splice between
STA 340 and STA 380. We are issuing this AD to prevent cracking in the
fuselage skin, which could result in rapid decompression and loss of
structural integrity of the airplane.
DATES: This AD becomes effective April 2, 2009.
On May 20, 2008 (73 FR 29042, May 20, 2008), the Director of the
Federal Register approved the incorporation by reference of Boeing
Alert Service Bulletin 747-53A2748, dated May 9, 2008.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-
2207; telephone 206-544-9990; fax 206-766-5682; e-mail DDCS@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: 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
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2008-10-15, amendment
39-15522 (73 FR 29042, May 20, 2008). The existing AD applies to
certain Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F,
747-300, 747SR, and 747SP series airplanes. That NPRM was published in
the Federal
[[Page 8738]]
Register on September 23, 2008 (73 FR 54755). That NPRM proposed to
continue to require an inspection to determine if acceptable external
skin doublers are installed at the stringer 6 (S-6) lap splices,
between station (STA) 340 and STA 400. For airplanes without the
acceptable external skin doublers, that NPRM also proposed to continue
to require repetitive related investigative actions and corrective
actions if necessary. That NPRM also proposed to require a previously
optional terminating modification for the repetitive related
investigative actions.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the single comment that has
been received on the NPRM. The commenter, Boeing, concurs with the
NPRM.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD as proposed.
Costs of Compliance
The inspection for acceptable external skin doublers that is
required by AD 2008-10-15 and retained in this AD takes about 2 work
hours per airplane, at an average labor rate of $80 per work hour.
Based on these figures, the estimated cost of the inspection for U.S.
operators is $27,840, or $160 per airplane.
The cost for the terminating action depends on the results of the
inspections. Therefore, we cannot calculate those costs because we do
not know what doubler conditions operators will find.
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 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this 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.
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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-15522 (73 FR 29042, May 20, 2008) and by adding
the following new airworthiness directive (AD):
2009-04-16 Boeing: Amendment 39-15822. Docket No. FAA-2008-1006;
Directorate Identifier 2008-NM-110-AD.
Effective Date
(a) This AD becomes effective April 2, 2009.
Affected ADs
(b) This AD supersedes AD 2008-10-15.
Applicability
(c) This AD applies to Boeing Model 747-100, 747-100B, 747-200B,
747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes,
certificated in any category; as identified in Boeing Alert Service
Bulletin 747-53A2748, dated May 9, 2008.
Unsafe Condition
(d) This AD results from a report of cracked fastener holes at
the right stringer 6 (S-6) lap splice between station (STA) 340 and
STA 380. We are issuing this AD to prevent cracking in the fuselage
skin, which could result in rapid decompression and loss of
structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 2008-10-15
Service Bulletin Reference Paragraph
(f) The term ``alert service bulletin,'' as used in this AD,
means the Accomplishment Instructions of Boeing Alert Service
Bulletin 747-53A2748, dated May 9, 2008.
Inspection for Acceptable External Skin Doublers
(g) For airplanes identified as Group 1, Configuration 2, in
Boeing Alert Service Bulletin 747-53A2748, dated May 9, 2008: At the
latest of the times specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD, do an external general visual inspection to
determine if acceptable external skin doublers are installed at the
left- and right-side S-6 lap splices, in accordance with Part 1 of
the alert service bulletin.
(1) Prior to the accumulation of 10,000 total flight cycles.
(2) Within 8,000 flight cycles after a modification was done in
accordance with Boeing Service Bulletin 747-53-2253.
(3) Within 15 days or 100 flight cycles after May 20, 2008 (the
effective date of AD 2008-10-15), whichever occurs first.
Acceptable External Skin Doublers Found at Both Sides
(h) If, during the inspection required by paragraph (g) of this
AD, acceptable external skin doublers in accordance with the alert
service bulletin are found installed at both the left- and right-
side S-6 lap splices, no further work is required by this AD.
Acceptable External Skin Doublers Not Found--Repetitive Related
Investigative Actions and Corrective Actions
(i) If, during the inspection required by paragraph (g) of this
AD, acceptable external skin doublers in accordance with alert
service bulletin are not found installed at either the left- or
right-side S-6 lap splice: Before further flight, do all applicable
related investigative and corrective actions by doing all actions
specified in Part 2 of the alert service bulletin. Repeat the
applicable related investigative actions thereafter at intervals not
to exceed 300 flight cycles until the modification specified in
paragraph (j) of this AD is done.
[[Page 8739]]
New Requirement of This AD
Terminating Modification
(j) If, during the inspection required by paragraph (g) of this
AD, acceptable external skin doublers as specified in the alert
service bulletin are not found installed at either the left- or
right-side S-6 lap splice: Within 3,000 flight cycles after doing
the initial related investigative actions in paragraph (i) of this
AD, or within 300 flight cycles after the effective date of this AD,
whichever occurs later, install acceptable external skin doublers at
both the left- and right-side S-6 lap splices, as applicable. The
installation of the acceptable skin doublers is required on the side
of the airplane that does not have the acceptable doublers already.
The installation includes doing an open-hole high-frequency eddy
current (HFEC) inspection of the skin for cracking, and trimming out
cracking as applicable. Do all actions in accordance with the alert
service bulletin. Doing this installation terminates the repetitive
related investigative actions required by paragraph (i) of this AD.
Note 1: The alert service bulletin refers to Boeing Service
Bulletins 747-53-2253, Revision 3, dated March 24, 1994; and 747-53-
2272, Revision 18, dated May 16, 2002; as additional sources of
service information for accomplishment of the modification
(installation of acceptable external skin doublers).
Note 2: AD 90-06-06, amendment 39-6490, requires, among other
actions, a modification as specified in Boeing Service Bulletin 747-
53-2253, dated December 14, 1984.
Note 3: AD 90-23-14, amendment 39-6801, requires inspections as
specified in Boeing Service Bulletin 747-53-2253, Revision 2, dated
March 29, 1990.
Alternative Methods of Compliance (AMOCs)
(k)(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, 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; 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
(l) You must use Boeing Alert Service Bulletin 747-53A2748,
dated May 9, 2008, to do the actions required by this AD, unless the
AD specifies otherwise.
(1) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2748, dated May 9, 2008, on May 20, 2008 (73 FR 29042, May 20,
2008).
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington
98124-2207; telephone 206-544-9990; fax 206-766-5682; e-mail
DDCS@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 February 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-3616 Filed 2-25-09; 8:45 am]
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