Airworthiness Directives; The Boeing Company Airplanes, 26720-26727 [2013-10905]
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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules
or Airbus Service Bulletin A340–29–4091
(for Model A340–200 and –300 series
airplanes) has been embodied in service:
Within 1,000 flight hours after the effective
date of this AD, do a general visual
inspection of the green, yellow, and blue
high pressure manifolds and check valves
having P/N CAR401 for any sign of rotation
of the check valve head, and for any signs of
hydraulic fluid leakage or seepage (including
black deposits), in accordance with the
instructions of Airbus Alert Operators
Transmission A29L001–12, dated October 11,
2012. Repeat the inspection thereafter at
interval not to exceed 900 flight hours.
(k) New Corrective Action for Certain
Airplanes
If, during any inspection required by
paragraph (j) of this AD, any sign of rotation
of the check valve head is found, or any sign
of hydraulic fluid leakage or seepage
(including black deposits) is found: Before
further flight, do all applicable corrective
actions, in accordance with the instructions
of Airbus Alert Operators Transmission
A29L001–12, dated October 11, 2012.
(l) No Terminating Action
Accomplishment of the corrective actions
required by this AD does not constitute
terminating action for the repetitive
inspections required by this AD.
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(m) Replacement Check Valve Torque Value
As of the effective date of this AD, at each
replacement of a check valve with a check
valve having P/N CAR401, apply a torque of
141 to 143 newton metre (N.m) (103.98 to
105.45 pounds-foot (lbf.ft)) during
installation.
(n) Credit for Previous Actions
(1) This paragraph restates the credit
specified in paragraph (g)(2)(iv) of AD 2009–
24–09, Amendment 39–16068 (74 FR 62208,
November 27, 2009). This paragraph provides
credit for actions required by paragraph
(g)(2)(i) of this AD, if those actions were
performed before December 14, 2009 (the
effective date of AD 2009–24–09), using
Airbus AOT A330–29A3111, dated
September 2, 2009 (for Model A330–200 and
–300 series airplanes); or AOT A340–
29A4086, dated September 2, 2009 (for
Model A340–200 and –300 series airplanes).
(2) This paragraph provides credit for
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Airbus AOT
A330–29A3111, dated September 2, 2009; or
Revision 1, dated October 8, 2009 (for Model
A330–200 and –300 series airplanes); or AOT
A340–29A4086, dated September 2, 2009; or
Revision 1, dated October 8, 2009 (for Model
A340–200 and –300 series airplanes). After
the effective date of this AD all inspections
and corrective actions, as required by
paragraph (i) of this AD, must be
accomplished in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A330–29–3111,
Revision 02, dated June 23, 2011, or Airbus
Mandatory Service Bulletin A340–29–4086,
Revision 02, dated June 23, 2011; as
applicable.
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(o) No Reporting
Although the service information specified
in paragraphs (o)(1) through (o)(5) of this AD
specifies to submit certain information to the
manufacturer, this AD does not include that
requirement.
(1) Airbus Alert Operators Transmission
A29L001–12, dated October 11, 2012.
(2) Airbus Mandatory Service Bulletin
A330–29–3111, Revision 02, dated June 23,
2011.
(3) Airbus Mandatory Service Bulletin
A340–29–4086, Revision 02, dated June 23,
2011.
(4) Airbus AOT A330–29A3111, Revision
1, dated October 8, 2009.
(5) Airbus AOT A340–29A4086, Revision
1, dated October 8, 2009.
(p) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, Transport Airplane Directorate, 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 International Branch, send it
to ATTN: Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1138; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter
must specifically reference this AD. AMOCs
approved for AD 2009–24–09, Amendment
39–16068 (74 FR 62208, November 27, 2009)
are approved as AMOCs for the
corresponding provisions of this AD, except
AMOC ANM–116–11–172 is not approved as
an AMOC for the corresponding provisions of
this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information European
Aviation Safety Agency Airworthiness
Directive 2012–0244R1, dated January 25,
2013; and the following service information;
for related information.
(i) Airbus Alert Operators Transmission
A29L001–12, dated October 11, 2012.
(ii) Airbus Mandatory Service Bulletin
A330–29–3111, Revision 02, dated June 23,
2011.
(iii) Airbus Mandatory Service Bulletin
A340–29–4086, Revision 02, dated June 23,
2011.
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(iv) Airbus AOT A330–29A3111, Revision
1, dated October 8, 2009.
(v) Airbus AOT A340–29A4086, Revision
1, dated October 8, 2009.
(2) For service information identified in
this AD, contact, Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330–A340@airbus.com;
Internet https://www.airbus.com. You may
review copies of the referenced service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. 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 Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–10908 Filed 5–7–13; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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
SUMMARY:
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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules
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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
https://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 https://
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
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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 https://
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
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26721
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,
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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules
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.
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.
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–
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
Action
Labor cost
Material type inspection and inspection for cracks
(retained actions from AD 2008–18–07,
Amendment 39-15664 (73 FR 56960, October
1, 2008)) (119 airplanes).
New Material type inspection and inspection for
cracks [new proposed action] (166 airplanes).
4 work-hours × $85 per
hour = $340 per inspection cycle.
$0
$340 per inspection
cycle.
$40,460 per inspection
cycle.
14 work-hours × $85
per hour = $1,190 per
inspection cycle.
$0
$1,190 per inspection
cycle.
$197,540 per inspection
cycle.
We estimate the following costs to do
any necessary on-condition actions that
Parts cost
Cost per product
would be required based on the results
of the proposed inspections. We have no
Cost on U.S. operators
way of determining the number of
aircraft that might need these actions:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Corner reveal removal and replacement [new proposed action].
17 work-hours × $85 per hour =
$1,445 per inspection cycle.
$9,525
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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.
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
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Cost per product
$10,970 per inspection cycle.
(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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules
§ 39.13
[Amended]
2. The FAA amends § 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.
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(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
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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
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26723
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
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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
VerDate Mar<15>2010
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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
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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.
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(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
VerDate Mar<15>2010
17:07 May 07, 2013
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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.
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(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
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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 onepiece 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;
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17:07 May 07, 2013
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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 twopiece 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
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AD, before further flight, replace the onepiece 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
E:\FR\FM\08MYP1.SGM
08MYP1
Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules
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 twopiece 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.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(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–ANMSeattle-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
VerDate Mar<15>2010
17:07 May 07, 2013
Jkt 229001
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
DEPARTMENT OF LABOR
Employee Benefits Security
Administration
29 CFR Part 2520
RIN 1210–AB20
Pension Benefit Statements
Employee Benefits Security
Administration, Department of Labor.
ACTION: Advance notice of proposed
rulemaking.
AGENCY:
The Department of Labor
(Department) is developing proposed
regulations regarding the pension
benefit statement requirements under
section 105 of the Employee Retirement
Income Security Act of 1974, as
amended (ERISA). This advance notice
of proposed rulemaking (ANPRM)
describes certain rules the Department
is considering as part of the proposed
regulations. The rules being considered
are limited to the pension benefit
statements required of defined
contribution plans. First, the
Department is considering a rule that
would require a participant’s accrued
SUMMARY:
PO 00000
Frm 00017
Fmt 4702
Sfmt 4702
26727
benefits to be expressed on his pension
benefit statement as an estimated
lifetime stream of payments, in addition
to being presented as an account
balance. Second, the Department also is
considering a rule that would require a
participant’s accrued benefits to be
projected to his retirement date and
then converted to and expressed as an
estimated lifetime stream of payments.
This ANPRM serves as a request for
comments on specific language and
concepts in advance of proposed
regulations. The Department intends to
consider all reasonable alternatives to
direct regulation, including whether
there is a way short of a regulatory
mandate that will ensure that
participants and beneficiaries get
constructive and helpful lifetime
income illustrations.
DATES: Comments are due on or before
July 8, 2013.
ADDRESSES: You may submit comments,
identified by RIN 1210–AB20, by one of
the following methods:
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
• Email: e-ORI@dol.gov. Include RIN
1210–AB20 in the subject line of the
message.
• Mail: Office of Regulations and
Interpretations, Employee Benefits
Security Administration, Room N–5655,
U.S. Department of Labor, 200
Constitution Avenue NW., Washington,
DC 20210, Attention: Pension Benefit
Statements Project.
Instructions: All submissions received
must include the agency name and
Regulation Identifier Number (RIN) for
this rulemaking. Comments received
will be posted without change to
https://www.regulations.gov and https://
www.dol.gov/ebsa, and made available
for public inspection at the Public
Disclosure Room, N–1513, Employee
Benefits Security Administration, 200
Constitution Avenue NW., Washington,
DC 20210, including any personal
information provided. Persons
submitting comments electronically are
encouraged not to submit paper copies.
FOR FURTHER INFORMATION CONTACT:
Suzanne Adelman or Tom Hindmarch at
(202) 693–8500. This is not a toll free
number.
SUPPLEMENTARY INFORMATION: This
ANPRM has two main sections followed
by Appendix A. The first section,
entitled ‘‘Background,’’ contains the
relevant statutory language on which
the Department is basing the ANPRM
and a discussion of the Department’s
general policy concern underlying the
ANPRM. The second section, entitled
‘‘Overview of Intended Regulations,’’
E:\FR\FM\08MYP1.SGM
08MYP1
]]>Agencies
[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]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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 https://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 https://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
