[Federal Register Volume 74, Number 154 (Wednesday, August 12, 2009)]
[Proposed Rules]
[Pages 40529-40534]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-19262]


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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]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 747-200C and -200F Series 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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[[Page 40530]]

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) that applies to certain Boeing Model 747-200C and -200F 
series airplanes. The existing 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 the initiation of certain repetitive 
inspections. This proposed AD would 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. This proposed AD would also 
provide a new optional modification, which would terminate certain 
repetitive inspections. This proposed 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 proposing 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: We must receive comments on this proposed AD by September 28, 
2009.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 <a href="/cdn-cgi/l/email-protection#cba6aee5a9a4aea8a4a68ba9a4aea2a5ace5a8a4a6"><span class="__cf_email__" data-cfemail="9ff2fab1fdf0fafcf0f2dffdf0faf6f1f8b1fcf0f2">[email protected]</span></a>; Internet 
https://www.myboeingfleet.com. You may review copies of the referenced 
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 or 425-227-
1152.

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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (telephone 800-647-5527) 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0684; 
Directorate Identifier 2008-NM-149-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed 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 proposed AD.

Discussion

    On March 31, 2006, we issued AD 2006-08-02, amendment 39-14556 (70 
FR 18618, April 12, 2006), for certain Boeing Model 747-200C and -200F 
series airplanes. That AD 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. That AD also 
provides optional modifications, which extend the threshold for 
initiating certain repetitive inspections. That AD resulted from new 
reports of cracks in the upper deck floor beams occurring at lower 
total flight cycles. We issued that AD to find and fix cracking in the 
upper chord of certain upper deck floor beams in Section 41. Such 
cracking could extend and sever the floor beams, which could result in 
rapid decompression and loss of controllability of the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2006-08-02, several operators of Boeing Model 
747-400D series airplanes have reported cracking in the floor panel 
attachment fastener holes of the upper chord of the upper deck floor 
beams at body stations (BS) 460 and 480, and at the upper chord of the 
floor beams in Section 42. The upper deck floor beams of Model 747-200C 
and 747-200F series airplanes are of similar type design to Model 747-
400D series airplanes at those locations; therefore, we have concluded 
that the unsafe condition also exists on Model 747-200C and 747-200F 
series airplanes. In addition, Boeing has done analysis that shows 
certain permanent fastener holes of the upper chord of certain upper 
deck floor beams in Section 41 are also susceptible to fatigue 
cracking.

Other Relevant Rulemaking

    On December 26, 2007, we issued AD 2004-07-22 R1, amendment 39-
15326 (73 FR 1052, January 7, 2008), 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, 747SR, and 747SP series airplanes. (A correction of 
the final rule was published in the Federal Register on February 14, 
2008 (73 FR 8589).) That AD requires that the FAA-approved maintenance 
inspection program be revised to include inspections that will give no 
less than the required damage tolerance rating for each structural 
significant item, and repair of cracked structure. We issued that AD to 
ensure the continued structural integrity of the affected Model 747 
series airplanes.

Relevant Service Information

    We have reviewed Boeing Alert Service Bulletin 747-53A2439, 
Revision 2, dated July 17, 2008 (``Revision 2 of the service 
bulletin''). (We referred to

[[Page 40531]]

Boeing Alert Service Bulletin 747-53A2439, Revision 1, dated March 10, 
2005, as the appropriate source of service information for 
accomplishing the actions required by AD 2006-08-02.) Revision 2 of the 
service bulletin adds procedures for repetitive open-hole or surface 
high-frequency eddy current (HFEC) inspections to find fatigue cracking 
in the upper chord of the upper deck floor beams at body stations (BS) 
460 and 480, and from BS 540 to 780 (specified as Area 5 in the service 
bulletin). Revision 2 of the service bulletin also adds procedures for 
inspections to find fatigue cracking in the permanent fastener holes of 
the upper chord of certain upper deck floor beams in Section 41.
    For airplanes on which any crack is found, Revision 2 of the 
service bulletin specifies the corrective action of repairing the crack 
before further flight. The repair depends on the location and extent of 
cracking and can involve oversizing the fastener hole, installing a 
repair strap or angle, or contacting Boeing for repair instructions.
    Revision 2 of the service bulletin also specifies post-repair 
inspections and corrective actions that include:
    <bullet> Repair of any cracking before further flight. For 
airplanes on which a crack is found in a previously repaired or 
modified area, the service bulletin specifies contacting Boeing for 
repair data.
    <bullet> An additional HFEC inspection for cracking of areas that 
have been repaired or modified.
    Revision 2 of the service bulletin also describes optional 
(alternative) modification procedures for airplanes on which no 
cracking is found. Accomplishing these modifications extends the 
threshold for initiating certain repetitive inspections.
    Revision 2 of the service bulletin defines the area for the new 
floor panel attachment fastener hole inspections as ``Area 5.'' The 
Area 5 inspections start at the latest of the following times:
    <bullet> Before the accumulation of 20,000 total flight cycles.
    <bullet> Within 1,000 flight cycles after the date of the service 
bulletin.
    <bullet> Within 2,000 flight cycles after the last surface HFEC 
inspection or 6,000 flight cycles after the last open-hole HFEC 
inspection done in accordance with Supplemental Structural Inspection 
Document (SSID) SSI F-19B only (required by AD 2004-07-22 R1).
    Revision 2 of the service bulletin also specifies additional 
inspection of permanent fastener holes in ``Areas 1, 2, 3 and 4.'' This 
new inspection starts at the later of the following times:
    <bullet> Before the accumulation of 15,000 total flight cycles.
    <bullet> Within 1,000 flight cycles after the date of the service 
bulletin.
    The repetitive inspection interval depends on the inspection method 
and previous repairs/modifications, and ranges from 2,000 to 6,000 
flight cycles for the surface/open-hole HFEC inspections.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition.
    Revision 2 of the service bulletin refers to Boeing Alert Service 
Bulletin 747-53A2696, dated October 16, 2008, for certain 
modifications. The actions in Boeing Alert Service Bulletin 747-53A2696 
have been approved as an alternative method of compliance (AMOC) with 
certain requirements of AD 2006-08-02.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to develop on other airplanes of the 
same type design. For this reason, we are proposing this AD, which 
would supersede AD 2006-08-02 and would retain the requirements of the 
existing AD. This proposed AD would also require accomplishing the 
actions specified in the service information described previously 
except as discussed under ``Differences Between the Proposed AD and the 
Service Bulletin.''

Differences Between the Proposed AD and the Service Bulletin

    Boeing Alert Service Bulletin 747-53A2439, Revision 2, dated July 
17, 2008, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
    <bullet> Using a method that we approve; or
    <bullet> Using data that meet the certification basis of the 
airplane, and that have been approved by an Authorized Representative 
for the Boeing Commercial Airplanes Delegation Option Authorization 
Organization whom we have authorized to make those findings.

Explanation of Changes Made to This AD

    We have added new paragraph (d) to this proposed AD specifying the 
Air Transport Association (ATA) of America code identifying the subject 
of the AD, and have re-identified the subsequent paragraphs 
accordingly.
    We have simplified paragraph (h)(1) of this proposed AD (which 
corresponds to paragraph (g)(1) of AD 2006-08-02) by referring to the 
``Alternative Methods of Compliance (AMOCs)'' paragraph of this AD for 
repair methods.
    We have revised paragraph (h)(1) of this proposed AD to allow any 
crack in the subject area to be repaired according to data that conform 
to the airplane's type certificate and that are approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization whom we have authorized to 
make such findings.

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 proposed AD.

                                                 Estimated Costs
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                                                                                Number of U.S.-
            Action               Work hours   Average labor  Cost per airplane    registered       Fleet cost
                                              rate per hour                        airplanes
----------------------------------------------------------------------------------------------------------------
Inspections (required by AD              29             $80  $2,320 per                     25  $58,000 per
 2006-08-02).                                                 inspection cycle.                  inspection
                                                                                                 cycle.
Inspection of Area 5 and                 78              80  $6,240 per                     25  $156,000 per
 permanent fastener hole in                                   inspection cycle.                  inspection
 Areas 1, 2, 3, and 4 (new                                                                       cycle.
 proposed action).
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[[Page 40532]]

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by removing amendment 39-14556 (70 FR 
18618, April 12, 2006) and adding the following new AD:

Boeing: Docket No. FAA-2009-0684; Directorate Identifier 2008-NM-
149-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by September 
28, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-08-02.

Applicability

    (c) This AD applies to Boeing 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), 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

[[Page 40533]]

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.

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 the 
service bulletin.
    (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 the service bulletin. 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 paragraphs (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--
------------------------------------------------------------------------
(1) The actions required by         Parts 1 and 2 of the Work
 paragraph (h) of this AD.           Instructions of Boeing Alert
                                     Service Bulletin 747-53A2439,
                                     Revision 1, dated March 10, 2005;
                                     as applicable.
(2) The applicable inspection of    Parts 1 and 6 of the Work
 the repaired area required by       Instructions of Boeing Alert
 paragraph (h)(1) of this AD.        Service Bulletin 747-53A2439,
                                     Revision 1, dated March 10, 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.
(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--
------------------------------------------------------------------------
(1) The actions required by         Part 1 (open-hole or surface HFEC
 paragraph (h) and (l) of this AD.   inspection, as applicable) of the
                                     Work Instructions of Boeing Alert
                                     Service Bulletin 747-53A2439,
                                     Revision 2, dated July 17, 2008.
(2) The applicable inspection of    Part 1 (open-hole HFEC inspection
 the repaired area required by       only) and Part 5 of the Work
 paragraph (h)(1) of this AD.        Instructions of Boeing Alert
                                     Service Bulletin 747-53A2439,
                                     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 required  Part 2 (upper chord repair at floor
 by paragraph (h)(1) of this AD.     panel attach holes) of the Work
                                     Instructions of Boeing Alert
                                     Service Bulletin 747-53A2439,
                                     Revision 2, dated July 17, 2008.
(4) The actions required by         Part 1 (open-hole HFEC inspection
 paragraph (i)(1) of this AD.        only), 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

[[Page 40534]]

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.
    (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 <a href="/cdn-cgi/l/email-protection#7d44503c3330502e181c09091118503c3e32503c30323e502f180c08180e090e3d1b1c1c531a120b"><span class="__cf_email__" data-cfemail="e2dbcfa3acafcfb1878396968e87cfa3a1adcfa3afada1cfb087939787919691a2848383cc858d94">[email protected]</span></a>.
    (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 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.

    Issued in Renton, Washington, on August 3, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-19262 Filed 8-11-09; 8:45 am]
BILLING CODE 4910-13-P


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