[Federal Register Volume 75, Number 248 (Tuesday, December 28, 2010)]
[Rules and Regulations]
[Pages 81427-81430]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-31992]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0232; Directorate Identifier 2009-NM-032-AD;
Amendment 39-16549; AD 2010-26-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-200C, -
200F, -400, -400D, and -400F 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 Model 747-200C, -200F, -400, -400D, and
-400F series airplanes. That AD currently requires repetitive
inspections for cracks in the overlapping (upper) skin of the upper
fastener row of the lap joints of the fuselage skin in sections 41, 42,
and 46; and related investigative and corrective actions, if necessary.
This new AD expands the inspection area in the existing AD, and adds a
modification of certain lap joints and certain post-repair inspections
of the lap joints. Accomplishing the modification would end the
repetitive inspections required by the existing AD for the length of
lap joint that is modified. This AD results from a structural review of
affected skin lap joints for widespread fatigue damage. We are issuing
this AD to prevent fatigue cracking in certain lap joints, which could
result in rapid depressurization of the airplane.
DATES: This AD becomes effective February 1, 2011.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of February 1,
2011.
On April 13, 2006 (71 FR 12122, March 9, 2006), the Director of the
Federal Register approved the incorporation by reference of a certain
other publication listed in the AD.
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 [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 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: Nicholas Han, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
917-6449; 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 2006-05-09, Amendment
39-14506 (71 FR 12122, March 9, 2006). The existing AD applies to
certain Model 747-200C, -200F, -400, -400D, and -400F series airplanes.
That NPRM was published in the Federal Register on March 18, 2010 (75
FR 13046). That NPRM proposed to continue to require repetitive
inspections for cracks in the overlapping (upper) skin of the upper
fastener row of the lap joints of the fuselage skin in Sections 41, 42,
and 46; and related investigative and corrective actions, if necessary.
That NPRM also proposed to expand the inspection area in the existing
AD, and add a modification of certain lap joints and certain post-
repair inspections of the lap joints. Accomplishing the modification
would end the repetitive inspections required by the existing AD.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments that have been
received on the NPRM.
Request To Revise Certain Language in Paragraph (k) of the NPRM
Boeing asked that we revise the language in paragraph (k) of the
NPRM to indicate that additional actions are required in the area of
the modification for operation beyond 15,000 total flight cycles after
doing the proposed modification. Boeing stated that Revision 2 of
Boeing Alert Service Bulletin 747-53A2499 is currently in work at the
Boeing Company, and that Revision 2 recommends accomplishing additional
actions after doing the modification.
Since this comment was submitted, we have received and reviewed
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010.
Boeing Alert Service Bulletin 747-53A2499, dated August 11, 2005; and
Revision 1, dated October 30, 2008; were referred to in the NPRM as the
appropriate source of service information for accomplishing the
actions. No more work is necessary for airplanes on which Boeing Alert
Service Bulletin 747-53A2499, Revision 1, dated October 30, 2008, was
used for doing the required actions. Revision 2 of this service
bulletin moves certain airplanes from Group 1 to Groups 15 and 16, adds
post-modification actions, and contains editorial changes.
We have revised paragraphs (c), (g), (h), (i), (j), and (k) of this
AD to refer to
[[Page 81428]]
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010.
In addition, we have removed Notes 1 and 2 of this AD since that
information is incorporated into Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010. We have also added a new paragraph
(n) to the AD to give credit for accomplishing the specified actions in
accordance with Boeing Alert Service Bulletin 747-53A2499, Revision 1,
dated October 30, 2008.
Although Boeing Service Bulletin 747-53A2499, Revision 2, dated
August 12, 2010, includes post-modification actions, this AD will not
mandate those actions. The threshold for the skin lap joint
modification mandated by this AD is 30,000 total flight cycles. Adding
15,000 flight cycles to the threshold would extend the compliance time
for the recommended additional actions to 45,000 total flight cycles.
We have determined that it is highly unlikely that a Model 747 airplane
will reach that number of total flight cycles. This determination also
takes into consideration the proposed wide spread fatigue damage (WFD)
operating rules imposing operating limits that could be significantly
lower than 45,000 total flight cycles.
In light of these factors, we have determined that this final rule
must be issued without any further delay due to the severity of the
unsafe condition addressed by this AD. Further rulemaking might be
issued in the future to mandate the additional actions included in
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12, 2010.
We have not changed the AD in this regard.
Request To Delay AD Pending New Service Information
Japan Airlines (JAL) asked that we delay issuance until the
manufacturer can release Revision 2 of Boeing Alert Service Bulletin
747-53A2499. JAL stated that Boeing has issued Service Bulletin
Information Notices 747-53A2499 IN 01, dated April 2, 2009; and 747-
53A2499 IN 02, dated September 10, 2009; to Boeing Alert Service
Bulletin 747-53A2499, Revision 1, dated October 30, 2008, to notify
operators of a typo and revised drawings. JAL noted that operators
cannot accomplish a correct inspection and modification unless the
information provided in Boeing Service Bulletin Information Notices
747-53A2499 IN 01 and 747-53A2499 IN 02 is used. JAL added that
including Revision 2 of this service bulletin would reduce unnecessary
burden on both operators and the manufacturer.
All Nippon Airways (ANA) also asked that the modification be done
in accordance with Revision 2 of Boeing Alert Service Bulletin 747-
53A2499 instead of Boeing Alert Service Bulletin 747-53A2499, Revision
1, dated October 30, 2008. ANA stated that it has already performed the
terminating modification at stringer 6 using Boeing Alert Service
Bulletin 747-53A2499, Revision 1, and had to request AMOCs during the
modification because certain drawings in Boeing Alert Service Bulletin
747-53A2499, dated August 11, 2005; and Revision 1, dated October 30,
2008; were not specific to the modification. ANA added that this will
reduce the AMOC requests to this proposed AD, in addition to reducing
the maintenance burden.
We partially agree with the commenters. We do not agree to delay
this AD, due to the severity of the unsafe condition. However, as
described previously, Boeing has issued Boeing Service Bulletin 747-
53A2499, Revision 2, dated August 12, 2010. Therefore, we have revised
the requirements in this AD to allow the use of Boeing Service Bulletin
747-53A2499, Revision 2, dated August 12, 2010, for accomplishing the
specified actions.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We also determined that
these changes will not increase the economic burden on any operator or
increase the scope of the AD.
Costs of Compliance
There are about 735 airplanes of the affected design in the
worldwide fleet. This AD affects 96 airplanes of U.S. registry.
The actions that are required by AD 2006-05-09 and retained in this
AD take about 541 work-hours per airplane, at an average labor rate of
$85 per work-hour. Based on these figures, the estimated cost of the
currently required actions is $45,985 per airplane, per inspection
cycle.
The new Area 2 inspections take about 124 work-hours per airplane,
at an average labor rate of $85 per work-hour. Based on these figures,
the estimated cost of the new inspections specified in this AD for U.S.
operators is $1,011,840, or $10,540 per airplane, per inspection cycle.
The new modification takes about 4,799 work hours per airplane, at
an average labor rate of $85 per work-hour. Required parts cost per
airplane will be minimal. Based on these figures, the estimated cost of
the new modification specified in this AD for U.S. operators is
$39,159,840, or $407,915 per airplane.
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:
[[Page 81429]]
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 39-14506 (71 FR 12122, March 9, 2006) and by adding
the following new airworthiness directive (AD):
2010-26-10 The Boeing Company: Amendment 39-16549. FAA-2010-0232;
Directorate Identifier 2009-NM-032-AD.
Effective Date
(a) This AD becomes effective February 1, 2011.
Affected ADs
(b) This AD supersedes AD 2006-05-09.
Applicability
(c) This AD applies to The Boeing Company Model 747-200C, -200F,
-400, -400D, and -400F series airplanes, certificated in any
category; as identified in Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from a structural review of affected skin
lap joints for widespread fatigue damage. The Federal Aviation
Administration is issuing this AD to prevent fatigue cracking in
certain lap joints, which could result in rapid depressurization of
the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-05-09, With Revised Service
Information
Initial Inspections and Related Investigative and Corrective Actions
(g) For airplanes identified in Boeing Alert Service Bulletin
747-53A2499, dated August 11, 2005: At the applicable time specified
in Table 1 of this AD, do an external surface high frequency eddy
current (HFEC), external low frequency eddy current (LFEC), and
internal LFEC inspection, as applicable, for cracks in the
overlapping (upper) skin of the upper fastener row of the lap joints
of the fuselage skin in sections 41, 42, and 46, and any applicable
related investigative and corrective actions by doing all of the
actions in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2499, dated August 11, 2005; Revision
1, dated October 30, 2008; or Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010. Do any applicable related
investigative and corrective actions before further flight. As of
the effective date of this AD, only Boeing Service Bulletin 747-
53A2499, Revision 2, dated August 12, 2010, may be used.
Table 1--Initial Compliance Time
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For airplanes on which Structural
Significant Items (SSIs) F-25G, F- Inspect--
25H, and F-25I--
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(1) Have not been inspected in Before the accumulation of 22,000
accordance with paragraph (i) of total flight cycles, or within
AD 2004-07-22 R1, Amendment 39- 1,000 flight cycles after April 13,
15326, using the HFEC method. 2006 (the effective date of AD 2006-
05-09), whichever occurs later.
(2) Have been inspected in Within 3,000 flight cycles after the
accordance with paragraph (i) of most recent supplemental structural
AD 2004-07-22 R1, using the HFEC inspection document (SSID)
method. inspection of each applicable
structural significant item (as
given in Boeing Document D6-35022,
``SSID for Model 747 Airplanes,''
Revision G, dated December 2000),
or within 1,000 flight cycles after
April 13, 2006, whichever occurs
later.
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Repetitive Inspections
(h) Repeat the applicable inspections required by paragraph (g)
of this AD thereafter at intervals not to exceed those specified in
paragraph 1.E., ``Compliance,'' (including the note) of Boeing Alert
Service Bulletin 747-53A2499, dated August 11, 2005; Revision 1,
dated October 30, 2008; or Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010. As of the effective date of this
AD, only Boeing Service Bulletin 747-53A2499, Revision 2, dated
August 12, 2010, may be used.
New Requirements of This AD
Repetitive Inspections/Investigative and Corrective Actions
(i) For all airplanes: Do an external HFEC inspection of the lap
joints in Sections 41, 42, and 46 for cracks, by doing all the
actions, including all applicable related investigative and
corrective actions, specified in the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12,
2010. Do the inspection at the applicable time specified in
paragraph 1.E. of Boeing Service Bulletin 747-53A2499, Revision 2,
dated August 12, 2010; except as required by paragraph (m) of this
AD. Do all applicable related investigative and corrective actions
before further flight. Repeat the inspection thereafter at the times
specified in paragraph 1.E. of Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010. Accomplishment of the inspections
required by this paragraph terminates the inspections required by
paragraphs (g) and (h) of this AD.
(j) For areas on which a lap joint repair was installed and the
repair doubler is greater than or equal to 40 inches long: Do
initial and repetitive internal HFEC inspections for cracks by doing
all the actions, including all applicable corrective actions,
specified in the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2499, Revision 2, dated August 12, 2010, except as
required by paragraph (l) of this AD. Do the inspections and
corrective actions at the times specified in paragraph 1.E. of
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12,
2010, except as required by paragraph (m) of this AD.
Terminating Action
(k) Modify the applicable lap joints in Sections 41 and 42 by
doing all the applicable actions specified in the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2499, Revision 2,
dated August 12, 2010, at the time specified in paragraph 1.E. of
Boeing Service Bulletin 747-53A2499, Revision 2, dated August 12,
2010; except as required by paragraphs (l) and (m) of this AD.
Accomplishing this modification terminates the repetitive
inspections of the skin lap joints in Sections 41 and 42 required by
paragraphs (i) and (j) of this AD for the length of lap joint that
is modified.
Exceptions to Service Bulletin Procedures
(l) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated
August 12, 2010, specifies to contact Boeing for appropriate action:
Before further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD.
(m) Where Boeing Service Bulletin 747-53A2499, Revision 2, dated
August 12, 2010, specifies a compliance time after the date of that
service bulletin, this AD requires compliance within the specified
compliance time after the effective date of this AD.
Credit for Actions Done Using Previous Service Information
(n) Actions done before the effective date of this AD in
accordance with Boeing Alert Service Bulletin 747-53A2499, Revision
1, dated October 30, 2008, are acceptable for compliance with the
corresponding requirements of this AD.
[[Page 81430]]
Alternative Methods of Compliance (AMOCs)
(o)(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: Nicholas Han, Aerospace Engineer, Airframe Branch, ANM-120S,
FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 917-6449; fax (425) 917-6590. Information may
be e-mailed 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) or other person 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 2006-05-09
are approved as alternative methods of compliance with the
corresponding requirements of this AD.
Material Incorporated by Reference
(p) You must use Boeing Alert Service Bulletin 747-53A2499,
dated August 11, 2005; or Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010; as applicable; 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 Boeing Service Bulletin 747-53A2499,
Revision 2, dated August 12, 2010, under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Boeing Alert Service Bulletin 747-
53A2499, dated August 11, 2005, on April 13, 2006 (71 FR 12122,
March 9, 2006).
(3) 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.
(4) 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.
(5) 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 December 13, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-31992 Filed 12-27-10; 8:45 am]
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