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[Federal Register Volume 78, Number 89 (Wednesday, May 8, 2013)]
[Proposed Rules]
[Pages 26720-26727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-10905]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0366; Directorate Identifier 2011-NM-024-AD]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 
747SR series airplanes. The existing AD requires, for certain 
airplanes, inspection to determine the material of a main entry door 
(MED) reveal; repetitive inspections of certain reveals for cracking; a 
detailed inspection of certain reveals for a sharp edge and cracking; 
and corrective action if necessary. That AD also allows a certain 
replacement as an optional action for certain inspections of certain 
airplanes. Since we issued that AD, an operator reported a crack found 
in a 6061 machined aluminum one-piece corner reveal. This proposed AD 
would add, for certain airplanes, an inspection to determine material 
type of MED reveals, repetitive inspections for cracking of 6061 
machined aluminum one-piece corner reveals, and replacement with 6061 
machined aluminum two-piece corner reveals if necessary. This

[[Page 26721]]

proposed AD would also allow replacement with two-piece corner reveals 
as an option for certain repetitive inspections. This proposed AD would 
also revise the applicability by removing a certain airplane. We are 
proposing this AD to detect and correct fatigue cracking of the lower 
forward corner reveal of the number 3 MEDs, which could lead to the 
door escape slide departing the airplane when the door is opened and 
the slide is deployed, and consequent injuries to passengers and crew 
using the door escape slide during an emergency evacuation.

DATES: We must receive comments on this proposed AD by June 24, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     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.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed 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; 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.

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 (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Bill Ashforth, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office 
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: (425) 917-
6432; fax: (425) 917-6590; email: bill.ashforth@faa.gov.

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-2013-0366; 
Directorate Identifier 2011-NM-024-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 August 20, 2008, we issued AD 2008-18-07, Amendment 39-15664 (73 
FR 56960, October 1, 2008), for certain The Boeing Company Model 747-
100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-
400D, and 747SR series airplanes. The existing AD requires, for certain 
airplanes, an inspection to determine the material of an MED reveal; 
repetitive inspections of certain reveals for cracking; a detailed 
inspection of certain reveals for a sharp edge and cracking; and 
corrective action if necessary. That AD also allows a certain 
replacement as an optional action for certain inspections of certain 
airplanes. The existing AD resulted from reports of cracking and/or a 
sharp edge in the lower forward corner reveal of the number 3 MEDs. We 
issued that AD to detect and correct fatigue cracking of the lower 
forward corner reveal of the number 3 MEDs, which could lead to the 
door escape slide departing the airplane when the door is opened and 
the slide is deployed, and possible consequent injuries to passengers 
and crew using the door escape slide during an emergency evacuation.

Actions Since Existing AD (73 FR 56960, October 1, 2008) Was Issued

    Since we issued AD 2008-18-07, Amendment 39-15664 (73 FR 56960, 
October 1, 2008), an operator reported a crack found in a 6061 machined 
aluminum one-piece corner reveal. Certain airplanes were equipped with 
either 356 cast aluminum or 6061 machined aluminum one-piece corner 
reveals at delivery. The existing AD allowed 356 cast aluminum reveals 
to be replaced with one-piece machined aluminum corner reveals. We have 
determined that inspections are necessary on airplanes having these 
one-piece reveals.

Relevant Service Information

    AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), 
referred to Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 1, dated February 13, 2007, as the appropriate source of 
service information for the required actions. Boeing has since revised 
this service information.
    We reviewed Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010. No new airplanes were added to the 
effectivity of Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, but airplane groups were changed 
based on the material composition of the corner reveals. This service 
information describes procedures for a material type inspection of one-
piece or two-piece corner reveals; inspection for sharp edges and 
cracking; and replacement of reworked 356 cast aluminum corner reveals 
and 6061 machined aluminum one-piece corner reveals with 6061 machined 
aluminum two-piece corner reveals, which would eliminate the need for 
repetitive inspections.
    Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010, also specifies a revised effectivity that 
clarifies the cargo configuration exceptions by excluding airplanes 
modified to the Boeing converted freighter and large cargo freighter 
configurations and removing an exception for Groups 2 and 3 of 
airplanes modified to the special freighter configuration. This service 
information also removes line number (L/N) 1271, a Model 747-400F 
series airplane, from the effectivity because it is a freighter 
airplane.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2008-
18-07, Amendment 39-15664 (73 FR 56960,

[[Page 26722]]

October 1, 2008). The proposed AD would require the actions specified 
in the service information described previously. The proposed AD would 
add, for certain airplanes, an inspection to determine material type of 
MED reveals, repetitive inspections for cracking of 6061 machined 
aluminum one-piece corner reveals, and replacement with 6061 machined 
aluminum two-piece corner reveals if necessary. This proposed AD would 
also allow replacement with two-piece corner reveals as an option for 
certain repetitive inspections. Also, the proposed AD would remove 
airplane L/N 1271, a Model 747-400F series airplane, from the AD 
applicability.

Changes To Existing AD (73 FR 56960, October 1, 2008)

    This proposed AD would retain all of the requirements of AD 2008-
18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008). However, we 
have removed the ``Service Bulletin Reference'' paragraph from this 
proposed AD. That paragraph was identified as paragraph (f) in AD 2008-
18-07. That paragraph provided operators with a one-time citation of 
the referenced service bulletin in AD 2008-18-07. Instead, we have 
provided the full service bulletin citation throughout this proposed 
AD.
    We have revised the heading and wording for paragraph (l) of this 
proposed AD, to clarify that the only exception to the procedures in 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007; and Boeing Special Attention Service Bulletin 
747-53-2460, Revision 2, dated December 22, 2010; is that, as of the 
effective date of this proposed AD, an operator's equivalent procedure 
may no longer be used without requesting approval of an alternative 
method of compliance (AMOC).
    We have also re-designated Notes 1 and 2 of AD 2008-18-07, 
Amendment 39-15664 (73 FR 56960, October 1, 2008), as paragraphs (p) 
and (q) of this proposed AD. This change does not affect the intent of 
those paragraphs.

Costs of Compliance

    We estimate that this proposed AD affects 166 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Material type inspection and       4 work-hours x $85             $0  $340 per inspection   $40,460 per
 inspection for cracks (retained    per hour = $340 per                cycle.                inspection cycle.
 actions from AD 2008-18-07,        inspection cycle.
 Amendment 39[dash]15664 (73 FR
 56960, October 1, 2008)) (119
 airplanes).
New Material type inspection and   14 work-hours x $85            $0  $1,190 per            $197,540 per
 inspection for cracks [new         per hour = $1,190                  inspection cycle.     inspection cycle.
 proposed action] (166 airplanes).  per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of the proposed 
inspections. We have no way of determining the number of aircraft that 
might need these actions:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                 Action                            Labor cost           Parts cost         Cost per product
----------------------------------------------------------------------------------------------------------------
Corner reveal removal and replacement     17 work-hours x $85 per           $9,525   $10,970 per inspection
 [new proposed action].                    hour = $1,445 per                          cycle.
                                           inspection cycle.
----------------------------------------------------------------------------------------------------------------

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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

[[Page 26723]]

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2013-0366; Directorate Identifier 
2011-NM-024-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by June 24, 
2013.

(b) Affected ADs

    This AD supersedes AD 2008-18-07, Amendment 39-15664 (73 FR 
56960, October 1, 2008).

(c) Applicability

    This AD applies to The Boeing Company Model 747-100, 747-100B, 
747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 
747SR series airplanes, certificated in any category, as identified 
in Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010, except airplanes that have been 
converted to an all-cargo configuration. The requirements of this AD 
also become applicable at the time when a converted airplane 
operating in an all-cargo configuration is converted back to a 
passenger or passenger/cargo configuration.

(d) Subject

    Air Transport Association (ATA) of America Code 53: Fuselage.

(e) Unsafe Condition

    This AD was prompted by a report of a crack found in a 6061 
machined aluminum one-piece corner reveal. We are proposing this AD 
to detect and correct fatigue cracking of the lower forward corner 
reveal of the number 3 main entry doors (MEDs), which could lead to 
the door escape slide departing the airplane when the door is opened 
and the slide is deployed, and consequent injuries to passengers and 
crew using the door escape slide during an emergency evacuation.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Actions for Group 3 Airplanes

    This paragraph restates the requirements of paragraph (g) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised service information. For airplanes identified as Group 3 
airplanes in Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 1, dated February 13, 2007: Before the accumulation of 
10,000 total flight cycles, or within 1,000 flight cycles after 
November 5, 2008 (the effective date of AD 2008-18-07), whichever 
occurs later, do a detailed inspection for cracking of the lower 
forward corner reveals, in accordance with Part 8 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 2 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
As of the effective date of this AD, only Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
may be used to accomplish the actions required by this paragraph.
    (1) If no cracking is found, repeat the inspection thereafter at 
intervals not to exceed 6,000 flight cycles until a new or reworked 
two-piece reveal is installed in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
As of the effective date of this AD, only Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
may be used to accomplish the actions required by this paragraph. No 
further action is required by this paragraph for that location only 
after the replacement.
    (2) If cracking is found, do the replacement specified in 
paragraph (g)(2)(i) or (g)(2)(ii) of this AD.
    (i) Before further flight, replace the reveal with a new or 
reworked two-piece reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
No further action is required by this paragraph for that location 
only after the replacement. As of the effective date of this AD, 
only Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010, may be used to accomplish the actions 
required by this paragraph.
    (ii) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 4 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010. Before the accumulation of 10,000 flight 
cycles since new on the replacement reveal, do the inspection for 
cracking specified in Part 8 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007; or Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. Repeat the inspection 
thereafter at intervals not to exceed 6,000 flight cycles until a 
new or reworked two-piece reveal is installed in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in paragraph (g)(2) of this AD. No further action is 
required by this paragraph for that location only after the 
replacement with a two-piece reveal. As of the effective date of 
this AD, only Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, may be used to accomplish the 
actions required by this paragraph.

(h) Retained Actions for Group 2 Airplanes

    This paragraph restates the requirements of paragraph (h) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised service information. For airplanes identified as Group 2 
airplanes in Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 1, dated February 13, 2007; or Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010: 
Before the accumulation of 1,500 total flight cycles, or within 
1,000 flight cycles after November 5, 2008 (the effective date of AD 
2008-18-07), whichever occurs later, do the inspection specified in 
paragraph (j) of this AD.

(i) Retained Actions for Group 1, Configuration 2 Airplanes

    This paragraph restates the requirements of paragraph (i) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised service information. For airplanes identified as Group 1, 
Configuration 2 airplanes in Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010: Within 1,500 flight cycles after the lower 
forward corner reveal was last replaced, or 1,000 flight cycles 
after November 5, 2008 (the effective date of AD 2008-18-07), 
whichever occurs later, do the inspection specified in paragraph (j) 
of this AD.

(j) Retained Inspection for Cracking and Sharp Edge

    This paragraph restates the requirements of paragraph (j) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised service information. At the applicable times specified in 
paragraphs (h) and (i) of this AD: Do a detailed inspection of the 
lower forward corner reveal for cracking and a sharp edge, in 
accordance with Part 5 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 1 and Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. As of the effective date 
of this AD, only Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010, may be used to accomplish 
the actions required by this paragraph.
    (1) If no cracking and no sharp edge are found, before the 
accumulation of 10,000 flight cycles on the lower forward corner 
reveal since new, or within 6,000 flight

[[Page 26724]]

cycles after doing the inspection required by paragraph (j) of this 
AD, whichever occurs later, do a detailed inspection for cracking, 
in accordance with Part 8 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007; or Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. Inspect thereafter at 
intervals not to exceed 6,000 flight cycles, until a new or reworked 
two-piece reveal is installed in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
If any cracking is found during any inspection required by this 
paragraph, before further flight, do the actions specified in 
paragraph (j)(3) of this AD. No further action is required by this 
paragraph for that location only after the replacement with a two-
piece reveal. As of the effective date of this AD, only Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010, may be used to accomplish the actions required by 
this paragraph.
    (2) If no cracking is found, but a sharp edge is found, do the 
actions specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD.
    (i) Before further flight, replace the lower forward corner 
reveal with a new or reworked two-piece reveal, in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. No further action is required by this paragraph 
for that location only after the replacement. As of the effective 
date of this AD, only Boeing Special Attention Service Bulletin 747-
53-2460, Revision 2, dated December 22, 2010, may be used to 
accomplish the actions required by this paragraph.
    (ii) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 4 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010. Before the accumulation of 10,000 flight 
cycles on the replacement reveal since new, do the inspection for 
cracking, in accordance with Part 8 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Inspect 
thereafter at intervals not to exceed 6,000 flight cycles, until a 
new or reworked two-piece reveal is installed in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in paragraph (j)(3) of this AD. No further action is 
required by this paragraph for that location only after the 
replacement with a two-piece reveal. As of the effective date of 
this AD, only Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, may be used to accomplish the 
actions required by this paragraph.
    (3) If cracking is found, do the actions specified in paragraph 
(j)(3)(i) or (j)(3)(ii) of this AD.
    (i) Before further flight, replace the reveal with a new or 
reworked two-piece reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
No further action is required by this paragraph for that location 
only after the replacement. As of the effective date of this AD, 
only Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010, may be used to accomplish the actions 
required by this paragraph.
    (ii) Before further flight, replace the lower forward corner 
reveal with a new or reworked one-piece machined aluminum reveal 
without a sharp edge, in accordance with Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 4 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
Before the accumulation of 10,000 flight cycles since new on the 
replacement reveal, do the inspection for cracking, in accordance 
with Part 8 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 2 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. Inspect thereafter at intervals not to exceed 
6,000 flight cycles, until a new or reworked two-piece reveal is 
installed in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Part 3 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. If any 
cracking is found during any inspection required by this paragraph, 
before further flight, do the actions required by paragraph (j)(3) 
of this AD. No further action is required by this paragraph for that 
location only after the replacement with a two-piece reveal. As of 
the effective date of this AD, only Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, may be 
used to accomplish the actions required by this paragraph.

(k) Retained Actions for Group 1, Configuration 1 Airplanes

    This paragraph restates the requirements of paragraph (k) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised service information. For airplanes identified as Group 1, 
Configuration 1 airplanes in Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007: Before 
the accumulation of 1,500 total flight cycles, or within 1,000 
flight cycles after November 5, 2008 (the effective date of AD 2008-
18-07), whichever occurs later, do a material type inspection to 
determine if the lower forward corner reveals are castings, in 
accordance with Part 1 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 6 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010. As an alternative to the material type 
inspection, replacing a reveal with a new or reworked two-piece 
lower forward corner reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010; 
is terminating action for the requirements of this paragraph for 
that location only. As of the effective date of this AD, only Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010, may be used to accomplish the actions required by 
this paragraph.
    (1) If the forward corner reveal is not a casting: Before 
further flight, do the actions specified in paragraph (j) of this AD 
except for the inspection for a sharp edge.
    (2) If the forward corner reveal is a casting: Before the 
accumulation of 7,000 total flight cycles, within 2,000 flight 
cycles after November 5, 2008 (the effective date of AD 2008-18-07), 
or within 3,000 flight cycles since the forward corner reveal was 
inspected as specified in Boeing Service Bulletin 747-53A2378, 
Revision 3, dated August 11, 2005; or Boeing Service Bulletin 747-
53A2378, Revision 4, dated June 10, 2010; whichever occurs latest; 
do a detailed inspection for cracking of the lower forward corner 
reveal, in accordance with Part 1 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 747-53-2460, Revision 
1, dated February 13, 2007; or Part 2 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. As of the effective date 
of this AD, only Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010, may be used to accomplish 
the actions required by this paragraph.

[[Page 26725]]

    (i) If no cracking is found: Repeat the inspection specified in 
paragraph (k)(2) of this AD thereafter at intervals not to exceed 
3,000 flight cycles until a new or reworked two-piece lower forward 
corner reveal is installed in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
No further action is required by this paragraph for that location 
only after the replacement.
    (ii) If cracking is found: Do the actions specified in paragraph 
(k)(2)(ii)(A), (k)(2)(ii)(B), or (k)(2)(ii)(C) of this AD.
    (A) Before further flight, weld repair the reveal, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 4 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. Repeat the inspection specified in paragraph 
(k)(2) of this AD thereafter at intervals not to exceed 3,000 flight 
cycles until a new or reworked two-piece reveal is installed in 
accordance with Part 2 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010. No further action is required by this 
paragraph for that location only after the replacement. As of the 
effective date of this AD, only Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, may be 
used to accomplish the actions required by this paragraph.
    (B) Before further flight, replace the reveal with a new or 
reworked two-piece reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
No further action is required by this paragraph for that location 
only after the replacement. As of the effective date of this AD, 
only Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010, may be used to accomplish the actions 
required by this paragraph.
    (C) Before further flight, replace the reveal with a new or 
reworked one-piece machined aluminum reveal without a sharp edge, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 1, dated 
February 13, 2007; or Part 4 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010. Before the accumulation of 10,000 flight 
cycles since new on the replacement reveal, do the inspection for 
cracking, in accordance with Part 8 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Inspect 
thereafter at intervals not to exceed 6,000 flight cycles, until a 
new or reworked two-piece reveal is installed in accordance with 
Part 2 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Part 3 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. If any cracking is found during any inspection 
required by this paragraph, before further flight, do the actions 
specified in paragraph (k)(2)(ii)(B) or (k)(2)(ii)(C) of this AD. No 
further action is required by this paragraph for that location only 
after the replacement with a two-piece reveal. As of the effective 
date of this AD, only Boeing Special Attention Service Bulletin 747-
53-2460, Revision 2, dated December 22, 2010, may be used to 
accomplish the actions required by this paragraph.

(l) Retained Requirement Regarding Operator's Equivalent Procedure

    This paragraph restates the requirements of paragraph (l) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008). 
Although Step 5 of Figure 8 of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007, specifies 
that operators may accomplish the actions in accordance with ``an 
operator's equivalent procedure,'' this AD does not allow using an 
``operator equivalent procedure unless approved as an alternative 
method of compliance in accordance with paragraph (w) of this AD.

(m) Retained Provisions for Compliance With AD 2007-12-11, Amendment 
39-15089 (72 FR 31984, June 11, 2007), for MED 3 Only

    This paragraph restates the provisions of paragraph (m) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), with 
revised information. Accomplishment of the applicable repair 
required by AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 
1, 2008), constitutes compliance with the repair of the lower 
forward corner casting (reveal) of the number 3 MEDs only, as 
required by paragraph (q)(2)(ii) of AD 2007-12-11, Amendment 39-
15089 (72 FR 31984, June 11, 2007), which specifies the actions must 
be done in accordance with Boeing Service Bulletin 747-53A2378, 
Revision 1, dated March 10, 1994; Boeing Service Bulletin 747-
53A2378, Revision 3, dated August 11, 2005; or Boeing Service 
Bulletin 747-53A2378, Revision 4, dated June 10, 2010. As of the 
effective date of this AD, only Boeing Service Bulletin 747-53A2378, 
Revision 4, dated June 10, 2010, may be used to accomplish the 
actions specified in this paragraph. Accomplishment of the actions 
of this AD does not terminate the remaining requirements of AD 2007-
12-11.

(n) Retained Parts Installation Prohibition (Cast 356 Aluminum) Reveals

    This paragraph restates the requirement of paragraph (n) of AD 
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008). As of 
November 5, 2008 (the effective date of AD 2008-18-07), no person 
may install a door lower forward corner reveal made of cast 356 
aluminum on any airplane at a location specified by AD 2008-18-07.

(o) Retained Parts Installation Limitation (Machined 6061 Aluminum) 
Reveals

    This paragraph restates the limitation specified by paragraph 
(o) of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 
2008), with revised service information. As of November 5, 2008 (the 
effective date of AD 2008-18-17), no person may install a door lower 
forward corner reveal made of machined 6061 aluminum on any airplane 
at a location specified by this AD, unless it has been confirmed/
reworked to be without a sharp edge, in accordance with Part 5 of 
the Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or Part 1 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
As of the effective date of this AD, only Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
may be used to accomplish the actions required by this paragraph.

(p) Retained Optional Rework of One-Piece and Two-Piece Machined 6061 
Aluminum Reveals

    This paragraph restates the information provided in ``Note 1'' 
of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), 
with revised information. For the purpose of this AD, a one-piece 
machined 6061 aluminum reveal may be reworked into a two-piece 
reveal in accordance with the Accomplishment Instructions of the 
applicable service bulletin identified in paragraph of (p)(1) or 
(p)(2) of this AD, after it was verified to be crack free and 
without a sharp edge, or after it was confirmed to be crack free and 
reworked to remove a sharp edge. As of the effective date of this 
AD, only Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, may be used to accomplish the 
actions provided by this paragraph.
    (1) Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 1, dated February 13, 2007.
    (2) Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010.

(q) Retained Optional Rework of One-Piece 6061 Aluminum Reveals With a 
Sharp Edge

    This paragraph restates the information provided in ``Note 2'' 
of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), 
with revised service information. For the purpose of this AD, a one-
piece machined 6061 aluminum reveal with a sharp edge may be 
reworked into a one-piece machined 6061 aluminum reveal without a

[[Page 26726]]

sharp edge, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Part 1 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010; after it 
is confirmed to be crack free in accordance with Part 5 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007, or Part 2 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
After the sharp edge is removed, the one-piece machined 6061 
aluminum reveal without a sharp edge may be further reworked into a 
two-piece reveal, in accordance with Part 7 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Part 5 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. As of the 
effective date of this AD, only Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, may be 
used to accomplish the actions specified by this paragraph.

(r) New Actions for Previously Inspected Group 4 Airplanes: Corner 
Reveal Not Replaced, or Replaced With Two-Piece Reveal

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have been inspected previously in accordance with the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 1, dated February 13, 2007; and on 
which the corner reveal either has not been replaced, or has been 
replaced with a two-piece reveal that was made by reworking an 
existing one-piece reveal: Before the accumulation of 7,000 total 
flight cycles, or within 3,000 flight cycles after the most recent 
inspection or rework done in accordance with Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 1, dated February 
13, 2007; or Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010; or within 1,000 flight cycles 
after the effective date of this AD, whichever occurs latest; do a 
material type inspection to determine if the corner reveal is a 
casting, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. Doing the inspection 
specified in this paragraph terminates the inspections required by 
paragraph (j) of this AD for these airplanes.
    (1) If, during any inspection required by paragraph (r) of this 
AD, any corner reveal is found to be a casting: Before further 
flight, do a detailed inspection for cracking of the corner reveal, 
in accordance with Part 2 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010; and repeat the inspection thereafter at 
intervals not to exceed 3,000 flight cycles until a new two-piece 
reveal in installed in accordance with the requirements of paragraph 
(r)(1)(i) of this AD. If any cracking is found, do the actions 
specified in paragraph (r)(1)(i) or (r)(1)(ii) of this AD.
    (i) Replace the cast reveal with a new 6061 machined aluminum 
two-piece corner reveal, before further flight, in accordance with 
Part 3 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (ii) Repair all cracking, before further flight, in accordance 
with Part 4 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (2) If, during any inspection required by paragraph (r) of this 
AD, any one-piece corner reveal is found to be installed and is not 
a casting: Before the accumulation of 10,000 total flight cycles; or 
within 6,000 flight cycles after the most recent inspection done in 
accordance with Boeing Special Attention Service Bulletin 747-53-
2460, Revision 1, dated February 13, 2007; or Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010; whichever occurs later; do a detailed inspection of the 
corner reveal for cracking, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Repeat 
the inspection for cracking thereafter at intervals not to exceed 
6,000 flight cycles until the corner reveal is replaced with a 6061 
machined aluminum two-piece corner reveal. If any cracking is found 
during any inspection required by paragraph (r)(2) of this AD, 
before further flight, replace the corner reveal with a 6061 
machined aluminum two-piece corner reveal, in accordance with Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010.

(s) New Actions for Previously Inspected Group 4 Airplanes: Corner 
Reveal Replaced With One-Piece Reveal

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have been inspected previously in accordance with Boeing 
Service Bulletin 747-53-2460, Revision 1, dated February 13, 2007, 
and on which the corner reveal has been replaced with a one-piece 
reveal: Within 10,000 flight cycles after the date the reveal was 
replaced with a one-piece corner reveal, do a detailed inspection 
for cracking of the corner reveal, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. Repeat 
the inspection for cracking thereafter at intervals not to exceed 
6,000 flight cycles until the corner reveal is replaced with a 6061 
machined aluminum two-piece corner reveal, in accordance with the 
requirements of paragraph (u) of this AD. If any cracking is found 
during any inspection required this paragraph of this AD, before 
further flight, replace the one-piece corner reveal with a 6061 
machined aluminum two-piece corner reveal, in accordance with Part 3 
of the Accomplishment Instructions of Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010.

(t) New Actions for Group 4 Airplanes: Not Previously Inspected or 
Changed

    For Group 4 airplanes identified in Boeing Special Attention 
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, 
that have not been previously inspected or changed in accordance 
with Boeing Special Attention Service Bulletin 747-53-2460, Revision 
1, dated February 13, 2007: Before the accumulation of 1,500 total 
flight cycles, or within 1,000 flight cycles after the effective 
date of this AD, whichever occurs later, do a material type 
inspection to determine if the lower forward corner reveal is made 
from 6061 machined aluminum plate or 356 aluminum casting, in 
accordance with Part 6 of the Accomplishment Instructions of Boeing 
Special Attention Service Bulletin 747-53-2460, Revision 2, dated 
December 22, 2010. Doing the inspection specified in this paragraph 
terminates the inspections required by paragraph (j) of this AD for 
these airplanes.
    (1) If, during any inspection required by paragraph (t) of this 
AD, any corner reveal is found to be a casting: Before the 
accumulation of 7,000 total flight cycles; or within 2,000 flight 
cycles after the effective date of this AD; or within 3,000 flight 
cycles after the most recent inspection of the MED 3 corner reveal 
was done in accordance with Boeing Service Bulletin 747-53A2378, 
Revision 4, dated June 10, 2010; whichever occurs latest; do a 
detailed inspection for cracking of the corner reveal, in accordance 
with Part 2 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010. Repeat the inspection for cracking thereafter at intervals 
not to exceed 3,000 flight cycles until the corner reveal is 
replaced with a 6061 machined aluminum two-piece corner reveal. If 
any cracking is found during any inspection required by this 
paragraph of this AD, before further flight, replace the casting 
with a 6061 machined aluminum two-piece corner reveal, in accordance 
with Part 3 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010.
    (2) If, during any inspection required by paragraph (t) of this 
AD, a corner reveal is found that is not a casting: Before further 
flight, do a detailed inspection for a sharp edge, in accordance 
with Part 1 of the Accomplishment Instructions of Boeing Special 
Attention Service Bulletin 747-53-2460, Revision 2, dated December 
22, 2010; and do a detailed inspection for cracking of the corner 
reveal, in accordance with Part 2 of the Accomplishment Instructions 
of Boeing Special Attention Service Bulletin 747-53-2460, Revision 
2, dated December 22, 2010. Repeat the inspection for cracking 
thereafter at intervals not to exceed 6,000 flight cycles until the 
corner reveal is replaced with a 6061 machined aluminum

[[Page 26727]]

two-piece corner reveal in accordance with the requirements of 
paragraph (u) of this AD.
    (i) If any sharp edge is found during any inspection required by 
paragraph (t)(2) of this AD, before further flight, rework the 
corner reveal, in accordance with Part 1 of the Accomplishment 
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010.
    (ii) If any cracking is found during any inspection required by 
paragraph (t)(2) of this AD, before further flight, replace the 
corner reveal with a 6061 machined aluminum two-piece corner reveal, 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010.

(u) New Terminating Action for Repetitive Inspections

    Installation of a 6061 machined aluminum two-piece corner reveal 
in accordance with Part 3 of the Accomplishment Instructions of 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2, 
dated December 22, 2010, terminates the repetitive inspections 
required by paragraphs (r), (s), and (t) of this AD.

(v) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) through (m) and (o) through (q) of this AD, if those 
actions were performed before the effective date of this AD using 
Boeing Special Attention Service Bulletin 747-53-2460, Revision 1, 
dated February 13, 2007; or Boeing Service Bulletin 747-53A2378, 
Revision 3, dated August 11, 2005; as applicable, which are not 
incorporated by reference in this AD.

(w) Alternative Methods of Compliance (AMOCs)

    (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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOC-REQUESTS@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (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) 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.
    (4) AMOCs previously approved in accordance with AD 2008-18-07, 
Amendment 39-15664 (73 FR 56960, October 1, 2008), are approved as 
AMOCs for the corresponding requirements of this AD for Group 2 and 
Group 3 airplanes identified in Boeing Special Attention Service 
Bulletin 747-53-2460, Revision 2, dated December 22, 2010. 
Previously approved AMOCs for Group 1 and Group 4 airplanes 
identified in Boeing Special Attention Service Bulletin 747-53-2460, 
Revision 2, dated December 22, 2010, are not approved for compliance 
with the actions required by this AD.

(x) Related Information

    (1) For more information about this AD, contact Bill Ashforth, 
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; 
phone: (425) 917-6432; fax: (425) 917-6590; email: 
bill.ashforth@faa.gov.
    (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; 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.

    Issued in Renton, Washington, on April 26, 2013.
Ali Bahrami,
Manager, Transport Aircraft Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-10905 Filed 5-7-13; 8:45 am]
BILLING CODE 4910-13-P
```