[Federal Register Volume 75, Number 63 (Friday, April 2, 2010)]
[Rules and Regulations]
[Pages 16651-16655]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-6546]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0684; Directorate Identifier 2008-NM-149-AD;
Amendment 39-16247; AD 2010-07-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Model 747-200C and -
200F 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 and -200F series
airplanes. That AD currently requires repetitive inspections to find
fatigue cracking in the floor panel attachment fastener holes of the
upper chord of certain upper deck floor beams in Section 41 (i.e., body
station 520 and forward), and repair if necessary. The existing AD also
provides optional modifications, which extend the threshold for
initiating certain repetitive inspections. This new AD requires
additional repetitive inspections to find fatigue cracking in the floor
panel attachment fastener holes of the upper chord of certain other
upper deck floor beams in Section 41 and Section 42 (i.e., aft of body
station 520); repetitive inspections to find fatigue cracking in the
permanent fastener holes of the upper chord of certain upper deck floor
beams in Section 41; and related investigative and corrective actions.
This new AD also provides a new optional modification, which terminates
certain repetitive inspections. This AD results from new reports of
cracking in the upper chord of the upper deck floor beams in Sections
41 and 42, and new analysis that shows the permanent fastener holes of
the upper chord of certain upper deck floor beams in Section 41 are
also susceptible to fatigue cracking. We are issuing this AD to detect
and correct cracking in the upper chord of the upper deck floor beams.
Such cracking could extend and sever the floor beams, which could
result in rapid decompression and loss of controllability of the
airplane.
DATES: This AD becomes effective May 7, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of May 7, 2010.
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 Docket 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 2006-08-02, amendment
39-14556 (70 FR 18618, April 12, 2006). The existing AD applies to
certain Model 747-200C and -200F series airplanes. That NPRM was
published in the Federal Register on August 12, 2009 (74 FR 40529).
That NPRM proposed to continue to require repetitive inspections to
find fatigue cracking in the floor panel attachment fastener
[[Page 16652]]
holes of the upper chord of certain upper deck floor beams in Section
41 (i.e., body station 520 and forward), and repair if necessary. That
NPRM also proposed to continue to provide optional modifications, which
extend the threshold for the initiation of certain repetitive
inspections. That NPRM also proposed to add repetitive inspections to
find fatigue cracking in the floor panel attachment fastener holes of
the upper chord of certain other upper deck floor beams in Section 41
and Section 42 (i.e., aft of body station 520); repetitive inspections
to find fatigue cracking in the permanent fastener holes of the upper
chord of certain upper deck floor beams in Section 41; and related
investigative and corrective actions. Additionally, that NPRM proposed
to provide a new optional modification, which would terminate certain
repetitive inspections.
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 from the single commenter.
Request To Revise Procedure Location Specified in Step (5) of Table 2
of the NPRM
Boeing requests that we revise Table 2 of the NPRM to update the
location in the referenced service bulletin for the modification
provided in Step (5) of Table 2 of the NPRM. Boeing points out that the
modification referred to in paragraph (h)(2) of AD 2006-08-02, provided
in Step (5) in Table 2 of the NPRM, was defined in Figure 5 of the
original issue of Boeing Alert Service Bulletin 747-53A2439, dated July
5, 2001. Boeing further points out that the instructions for this
modification were moved to Part 3 and Part 4 of the Work Instructions
of Revision 2, dated July 17, 2008, of Boeing Alert Service Bulletin
747-53A2439.
We do not agree to revise Table 2 of this AD. Step (5) of Table 2
references paragraph (i)(2) of this AD, and requires only the fastener
hole modification per Figure 5 and the open-hole high-frequency eddy
current (HFEC) inspection per Part 1 of the Work Instructions of Boeing
Alert Service Bulletin 747-53A2439, Revision 2, dated July 17, 2008.
The fastener hole slot repair per Part 4 of the Work Instructions of
Boeing Alert Service Bulletin 747-53A2439, Revision 2, dated July 17,
2008, is not required by paragraph (i)(2) of this AD. We note that the
fastener hole slot repair per Part 4 of the Work Instructions of Boeing
Alert Service Bulletin 747-53A2439, Revision 2, dated July 17, 2008,
which is referenced in Part 2 of the Work Instructions of Boeing Alert
Service Bulletin 747-53A2439, Revision 2, dated July 17, 2008, is
required by paragraph (i)(1) of this AD. We have made no change to the
final rule in this regard.
Request To Update Name of Boeing's Delegation Option Authorization
Organization
Boeing requests that we revise paragraphs (h)(1) and (o)(4) of the
NPRM to change ``Boeing Commercial Airplanes Delegation Option
Authorization Organization'' to ``Boeing Commercial Airplanes
Organization Designation Authorization Organization.'' Boeing points
out that they changed the name of this organization at the end of
August 2009.
We partially agree. Boeing Commercial Airplanes has received an
Organization Designation Authorization (ODA), which replaces their
previous designation as a Delegation Option Authorization holder. We
have revised paragraph (o)(4) of this AD to delegate the authority to
approve an alternative method of compliance for any repair required by
this AD to the Boeing Commercial Airplanes ODA rather than an
Authorized Representative under the former Delegation Option
Authorization (DOA) program. However, we have also revised paragraph
(h)(1) of this AD to reference paragraph (o) of this AD and to continue
to provide allowance for those operators that have used a repair
approved by a Boeing Company Designated Engineering Representative
(DER) or by an Authorized Representative for the Boeing Commercial
Airplanes DOA.
Explanation of Changes Made to This AD
We have revised this AD to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
Conclusion
We have carefully reviewed the available data, including the
comments that have been received, and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Explanation of Change to Costs of Compliance
Since issuance of the original NPRM, we have increased the labor
rate used in the Costs of Compliance from $80 per work-hour to $85 per
work-hour. The Costs of Compliance information, below, reflects this
increase in the specified hourly labor rate.
Costs of Compliance
There are about 68 airplanes of the affected design in the
worldwide fleet. The following table provides the estimated costs for
U.S. operators to comply with this AD.
Estimated Costs
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Average Number of U.S.-
Action Work hours labor rate Cost per airplane registered Fleet cost
per hour airplanes
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Inspections (required by AD 29 $85 $2,465 per 25 $61,625 per
2006-08-02). inspection cycle. inspection
cycle.
Inspection of Area 5 and 78 85 $6,630 per 25 $165,750 per
permanent fastener hole in inspection cycle. inspection
Areas 1, 2, 3, and 4 (new cycle.
required action).
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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.
[[Page 16653]]
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 39-14556 (70 FR 18618, April 12, 2006) and by adding
the following new airworthiness directive (AD):
2010-07-03 The Boeing Company: Amendment 39-16247. Docket No. FAA-
2009-0684; Directorate Identifier 2008-NM-149-AD.
Effective Date
(a) This AD becomes effective May 7, 2010.
Affected ADs
(b) This AD supersedes AD 2006-08-02, Amendment 39-14556.
Applicability
(c) This AD applies to The Boeing Company Model 747-200C and -
200F series airplanes, certificated in any category, as identified
in Boeing Alert Service Bulletin 747-53A2439, Revision 2, dated July
17, 2008.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from new reports of cracking in the upper
chord of the upper deck floor beams in Sections 41 and 42, and new
analysis that shows the permanent fastener holes of the upper chord
of certain upper deck floor beams in Section 41 are also susceptible
to fatigue cracking. We are issuing this AD to detect and correct
cracking in the upper chord of the upper deck floor beams. Such
cracking could extend and sever the floor beams, which could result
in rapid decompression and loss of controllability 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.
Requirements of AD 2006-08-02
Initial Compliance Time at a New Reduced Threshold
(g) At the earliest of the times specified in paragraphs (g)(1)
through (g)(3) of this AD, do the inspection required by paragraph
(h) of this AD.
(1) Before the accumulation of 22,000 total flight cycles, or
within 1,000 flight cycles after March 15, 2004 (the effective date
of AD 2004-03-11, which was superseded by AD 2006-08-02), whichever
occurs later.
(2) For airplanes with 17,000 or more total flight cycles as of
May 17, 2006 (the effective date of AD 2006-08-02): Before the
accumulation of 18,000 total flight cycles, or within 90 days after
May 17, 2006, whichever occurs later.
(3) For airplanes with fewer than 17,000 total flight cycles as
of May 17, 2006: Before the accumulation of 15,000 total flight
cycles, or within 1,000 flight cycles after May 17, 2006, whichever
occurs later.
Inspections at Reduced Intervals for Certain Floor Beams and Repair
(h) Do the applicable inspection to find fatigue cracking in the
upper chord of the upper deck floor beams as specified in Part 1
(Open-Hole High Frequency Eddy Current (HFEC) Inspection Method) or
Part 2 (Surface HFEC Inspection Method) of the Work Instructions of
Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001. Do
the inspections per the Boeing Alert Service Bulletin 747-53A2439,
dated July 5, 2001, except as provided by paragraph (k) of this AD.
Any combination of the applicable inspection methods specified in
Parts 1 and 2 may be used, provided that the corresponding
repetitive inspection interval is used.
(1) If any crack is found, before further flight, repair per
Part 3 (Upper Chord Repair) of the Work Instructions of Boeing Alert
Service Bulletin 747-53A2439, dated July 5, 2001; except where
Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001,
specifies to contact Boeing for appropriate action, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (o) of this AD or repair according
to data meeting the certification basis of the airplane approved by
a Boeing Company Designated Engineering Representative (DER) or by
an Authorized Representative for the Boeing Commercial Airplanes
Delegation Option Authorization Organization. For a repair method to
be approved by the Manager, Seattle Aircraft Certification Office
(ACO), FAA, as required by this paragraph, the Manager's approval
letter must specifically reference this AD. Do the applicable
inspection of the repaired area per Part 1 of the Work Instructions
of Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001, at
the applicable time per Part 3 of the Work Instructions of Boeing
Alert Service Bulletin 747-53A2439, dated July 5, 2001, and repeat
the applicable inspection at the applicable interval per Figure 1 of
Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001.
(2) If no crack is found, repeat the applicable inspection per
paragraph (h) of this AD at the applicable time specified in
paragraphs (h)(2)(i) through (h)(2)(iii) of this AD. As an option to
the repetitive inspections, accomplishment of paragraph (i)(1) or
(i)(2) of this AD, before further flight, extends the threshold for
the initiation of the repetitive inspections required by this
paragraph.
(i) If the immediately preceding inspection was conducted using
an open-hole HFEC inspection method: Conduct the next inspection of
that area within 3,000 flight cycles of the last inspection.
(ii) If the immediately preceding inspection was conducted using
a surface HFEC inspection method at stations 340 through 420
inclusive and station 500: Conduct the next inspection of that area
within 750 flight cycles of the last inspection.
(iii) If the immediately preceding inspection was conducted
using a surface HFEC inspection method at stations 440 and 520:
Conduct the next inspection of that area at the earlier of the times
specified in paragraphs (h)(2)(iii)(A) and (h)(2)(iii)(B) of this
AD, and thereafter at intervals not to exceed 250 flight cycles.
(A) Within 750 flight cycles since the last surface HFEC
inspection required by paragraph (h) of this AD.
(B) Within 250 flight cycles after May 17, 2006.
[[Page 16654]]
Optional Repair/Modification
(i) For areas on which the inspection required by paragraph (h)
of this AD is done per Part 1 of the Work Instructions of Boeing
Alert Service Bulletin 747-53A2439, dated July 5, 2001; and on which
no cracking is found: Accomplishment of the actions specified in
either paragraph (i)(1) or (i)(2) of this AD extends the threshold
for the initiation of the repetitive inspections required by
paragraph (h)(2) of this AD. For areas on which the inspection
required by paragraph (h) of this AD is done per Part 2 of Boeing
Alert Service Bulletin 747-53A2439, dated July 5, 2001; and on which
no cracking is found: Accomplishment of the actions specified in
paragraph (i)(1) of this AD extends the threshold for the initiation
of the repetitive inspections required by paragraph (h)(2) of this
AD.
(1) Do the applicable repair per Part 3 of the Work Instructions
of Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001,
except as provided by paragraph (k) of this AD. At the applicable
time specified in Table 1 of Part 3 of the Work Instructions of
Boeing Alert Service Bulletin 747-53A2439, dated July 5, 2001, do
the applicable inspection of the repaired area per Part 1 of the
Work Instructions of Boeing Alert Service Bulletin 747-53A2439,
dated July 5, 2001. Repeat the inspection thereafter within the
applicable interval of 3,000 flight cycles per Figure 1 of Boeing
Alert Service Bulletin 747-53A2439, dated July 5, 2001.
(2) Do the modification of the attachment hole of the floor
panel per Figure 5 of Boeing Alert Service Bulletin 747-53A2439,
dated July 5, 2001, except as provided by paragraph (k) of this AD.
Within 10,000 flight cycles after accomplishment of the
modification, do the inspection of the modified area per Part 1 of
the Work Instructions of Boeing Alert Service Bulletin 747-53A2439,
dated July 5, 2001. Repeat the inspection thereafter within the
applicable interval of 3,000 flight cycles per Figure 1 of Boeing
Alert Service Bulletin 747-53A2439, dated July 5, 2001.
Determining the Number of Flight Cycles for Compliance Time
(j) For the purposes of calculating the compliance threshold and
repetitive intervals for actions required by paragraph (g), (h), or
(i) of this AD: As of May 17, 2006 (the effective date of AD 2006-
08-02), all flight cycles, including the number of flight cycles in
which cabin differential pressure is at 2.0 pounds per square inch
(psi) or less, must be counted when determining the number of flight
cycles that have occurred on the airplane.
New Requirements of This AD
Applicable Revisions of Service Bulletins
(k) Use the information in Tables 1 and 2 of this AD, at the
applicable time specified in paragraphs (k)(1) and (k)(2) of this
AD, to determine the part of the applicable service bulletin to use
to accomplish the actions required by this AD.
(1) On or after May 17, 2006, but before the effective date of
this AD, use only the service information listed in Table 1 or Table
2 of this AD.
Table 1--Service Information Given in Boeing Alert Service Bulletin 747-
53A2439, Revision 1, Dated March 10, 2005
------------------------------------------------------------------------
Do-- In accordance with--
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(1) The actions required by Parts 1 and 2 of the Work Instructions of
paragraph (h) of this AD. Boeing Alert Service Bulletin 747-
53A2439, Revision 1, dated March 10,
2005; as applicable.
(2) The applicable inspection Parts 1 and 6 of the Work Instructions of
of the repaired area Boeing Alert Service Bulletin 747-
required by paragraph (h)(1) 53A2439, Revision 1, dated March 10,
of this AD. 2005; as applicable; at the applicable
time specified in Table 1 of Part 3 of
the Work Instructions of that service
bulletin.
(3) The actions required by Parts 1, 3, and 6 of the Work
paragraph (i)(1) of this AD. Instructions of Boeing Alert Service
Bulletin 747-53A2439, Revision 1, dated
March 10, 2005; as applicable.
(4) The actions required by Figure 5 and Part 1 of the Work
paragraph (i)(2) of this AD. Instructions of Boeing Alert Service
Bulletin 747-53A2439, Revision 1, dated
March 10, 2005; as applicable.
------------------------------------------------------------------------
(2) On or after the effective date of this AD, use only the
service information listed in Table 2 of this AD.
Table 2--Service Information Given in Boeing Alert Service Bulletin 747-
53A2439, Revision 2, Dated July 17, 2008
------------------------------------------------------------------------
Do-- In accordance with--
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(1) The actions required by Part 1 (open-hole or surface HFEC
paragraph (h) and (l) of inspection, as applicable) of the Work
this AD. Instructions of Boeing Alert Service
Bulletin 747-53A2439, Revision 2, dated
July 17, 2008.
(2) The applicable inspection Part 1 (open-hole HFEC inspection only)
of the repaired area and Part 5 of the Work Instructions of
required by paragraph (h)(1) Boeing Alert Service Bulletin 747-
of this AD. 53A2439, Revision 2, dated July 17,
2008; at the applicable time specified
in Table 1 of Part 2 of the Work
Instructions of that service bulletin.
(3) The applicable repair Part 2 (upper chord repair at floor panel
required by paragraph (h)(1) attach holes) of the Work Instructions
of this AD. of Boeing Alert Service Bulletin 747-
53A2439, Revision 2, dated July 17,
2008.
(4) The actions required by Part 1 (open-hole HFEC inspection only),
paragraph (i)(1) of this AD. Part 2, and Part 5 of the Work
Instructions of Boeing Alert Service
Bulletin 747-53A2439, Revision 2, dated
July 17, 2008.
(5) The actions required by Figure 5 and Part 1 (open-hole HFEC
paragraph (i)(2) of this AD. inspection only) of the Work
Instructions of Boeing Alert Service
Bulletin 747-53A2439, Revision 2, dated
July 17, 2008.
------------------------------------------------------------------------
New Inspections and Related Investigative and Corrective Actions
(l) For all airplanes, except as provided by paragraphs (k)(1)
and (k)(2) of this AD: At the applicable time specified in Paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 747-53A2439,
Revision 2, dated July 17, 2008, do the applicable open-hole or
surface HFEC inspections for fatigue cracking in the upper chord of
the upper deck floor beams in Area 5, and the inspection for fatigue
cracking in the permanent fastener holes of the upper chord of
certain upper deck floor beams in Areas 1, 2, 3, and 4, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2439, Revision 2, dated July 17, 2008. Do
all applicable related investigative and corrective actions before
further flight. Repeat the applicable inspection thereafter at the
applicable interval specified in Paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2439, Revision 2, dated July
17, 2008.
[[Page 16655]]
(1) Where Boeing Alert Service Bulletin 747-53A2439, Revision 2,
dated July 17, 2008, specifies a compliance time relative to the
date of issuance of that service bulletin, this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin 747-53A2439, Revision 2,
dated July 17, 2008, specifies contacting Boeing for repair data:
Before further flight, repair using a method approved in accordance
with the procedures specified in paragraph (o) of this AD.
Optional New Modification for Areas 1, 2, 3, and 4
(m) For areas 1, 2, 3, and 4 as defined in Boeing Alert Service
Bulletin 747-53A2439, Revision 2, dated July 17, 2008: Doing the
modification and post-modification actions specified in Boeing Alert
Service Bulletin 747-53A2696, dated October 16, 2008, terminates the
repetitive inspection requirements of paragraphs (g) and (h) of this
AD. Doing the modification and post-modification actions specified
in Boeing Alert Service Bulletin 747-53A2696, dated October 16,
2008, terminates the repetitive inspection requirements of paragraph
(l) of this AD, except at the upper deck floor beam at body station
(BS) 460 and 480 and the upper deck floor beams aft of BS 520.
No Reporting Requirement
(n) Although Boeing Alert Service Bulletin 747-53A2439, Revision
1, dated March 10, 2005; and Boeing Alert Service Bulletin 747-
53A2439, Revision 2, dated July 17, 2008; specify to submit certain
information to the manufacturer, this AD does not include that
requirement.
Alternative Methods of Compliance (AMOCs)
(o)(1) The Manager, Seattle 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 Aircraft
Certification Office, 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) AMOCs approved previously in accordance with AD 2006-08-02,
are approved as AMOCs for the corresponding provisions of this AD.
(4) 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
(p) You must use Boeing Alert Service Bulletin 747-53A2439,
Revision 2, dated July 17, 2008, to do the actions required by this
AD, unless the AD specifies otherwise. If you accomplish the new
optional actions specified by this AD, you must use Boeing Alert
Service Bulletin 747-53A2696, dated October 16, 2008, 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 March 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-6546 Filed 4-1-10; 8:45 am]
BILLING CODE 4910-13-P