Airworthiness Directives; The Boeing Company Airplanes, 77379-77384 [2014-30132]
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Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0366; Directorate
Identifier 2011–NM–024–AD; Amendment
39–18038; AD 2014–24–05]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) 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. This
AD was prompted by a report of a
cracked reveal made from a casting
found within a group of airplanes that
should have machined reveals made
only from 6061 aluminum. This AD
requires an inspection to determine the
material of the number 3 main entry
door (MED) corner reveal, repetitive
inspections of certain reveals for
cracking, and corrective action if
necessary. This AD also requires
repetitive inspections for cracking of
6061 machined aluminum one-piece
corner reveals, and replacement with
6061 machined aluminum two-piece
corner reveals if necessary, which
terminates certain repetitive
inspections. We are issuing 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: This AD is effective January 28,
2015.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 28, 2015.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, WA 98124–2207;
telephone 206–544–5000, extension 1;
fax 206–766–5680; Internet https://
www.myboeingfleet.com.You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
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availability of this material at the FAA,
call 425–227–1221.
crew using the door escape slide during
an emergency evacuation.
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
SUMMARY:
77379
Related AD
AD 2008–18–07, Amendment 39–
15664 (73 FR 56960, October 1, 2008),
requires, for 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, an inspection to determine
the material of a number 3 MED corner
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. AD 2008–18–07 allows
reveal replacement as an option to
certain inspections. AD 2008–18–07 was
prompted by reports of cracking and/or
a sharp edge in the lower forward corner
reveal of the number 3 MEDs. AD 2008–
18–07 refers 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
specified in that AD.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2013–
0366; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008–18–07,
Amendment 39–15664 (73 FR 56960,
October 1, 2008). AD 2008–18–07
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 NPRM published in the
Federal Register on May 8, 2013 (78 FR
26720). The NPRM was prompted by a
report of a cracked reveal made from a
casting found within a group of
airplanes that should have machined
reveals made only from 6061 aluminum.
The NPRM proposed to retain all the
requirements of AD 2008–18–07. The
NPRM also proposed to add, for certain
airplanes, an inspection to determine
the material of the number 3 MED
corner reveal, repetitive inspections for
cracking of 6061 machined aluminum
one-piece corner reveals, and
replacement with 6061 machined
aluminum two-piece corner reveals if
necessary, which terminates certain
repetitive inspections. We are issuing
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
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Explanation of Difference in
Requirements Between the NPRM (78
FR 26720, May 8, 2013) and This Final
Rule
In the NPRM (78 FR 26720, May 8,
2013), the FAA proposed to supersede
AD 2008–18–07, Amendment 39–15664
(73 FR 56960, October 1, 2008), to
reflect the changes in airplane groups
specified in revised service information,
Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010. However, based on
the comments received on the NPRM, it
became evident that it was difficult to
follow the numerous changes between
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, as well as in following the
corresponding actions specified in the
NPRM.
There are only two significant
changes in Boeing Special Attention
Service Bulletin 747–53–2460, Revision
2, dated December 22, 2010: (1)
Airplanes having line numbers 1038
through 1270 were moved from Group
2 to Group 4; and (2) for Group 4
airplanes, there are additional actions.
Therefore, for clarity, we have
determined that a less burdensome
approach is to revise this final rule to
include only the new actions for Group
4 airplanes. Instead of superseding AD
2008–18–07, Amendment 39–15664 (73
FR 56960, October 1, 2008), this final
rule is a stand-alone AD, applicable
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only to Group 4 airplanes as identified
in Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, except for those
airplanes that have been converted to an
all-cargo configuration. Airplanes
identified in the applicability of AD
2008–18–07 are still required to
continue to comply with the
requirements of that AD.
Since this AD does not supersede AD
2008–18–07, Amendment 39–15664 (73
FR 56960, October 1, 2008), paragraphs
(g) through (m), (p), (q), and (v) of the
NPRM (78 FR 26720, May 8, 2013) are
not included in this AD. Also, the
corresponding paragraph identifiers
have been redesignated in this final
rule, as listed in the following table:
REDESIGNATED PARAGRAPH
IDENTIFIERS
Requirement in the
proposed AD (78 FR
26720, May 8, 2013)
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(t)
(s)
(r)
(u)
(n)
(o)
(w)
Corresponding requirement in this AD
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(g).
(h).
(i).
(j).
(k).
(l).
(n).
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We have also revised paragraphs (n)
and (o) of the proposed AD (78 FR
26720, May 8, 2013) (redesignated as
paragraphs (k) and (l) of this AD) that
referred to ‘‘AD 2008–18–07.’’ In
paragraphs (k) and (l) of this AD, we
have referred to the current service
information, Boeing Special Attention
Service Bulletin 747–53–2460, Revision
2, dated December 22, 2010, instead of
AD 2008–18–07, Amendment 39–15664
(73 FR 56960, October 1, 2008), for the
locations where cast 356 aluminum
reveals and machined 6061 aluminum
reveals may not be installed. Paragraphs
(k) and (l) of this AD state that the parts
installation prohibition ends the parts
installation prohibitions specified in
paragraphs (n) and (o) of AD 2008–18–
07, Amendment 39–15664 (73 FR
56960, October 1, 2008).
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM (78 FR 26720,
May 8, 2013) and the FAA’s response to
each comment.
Request To Clarify the Cause of the
Unsafe Condition
Boeing asked that we clarify the cause
of the unsafe condition identified in
paragraph (e) of the proposed AD (78 FR
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26720, May 8, 2013). Boeing stated that
the report that prompted the proposed
supersedure of AD 2008–18–07,
Amendment 39–15664 (73 FR 56960,
October 1, 2008), involved a cracked
casting on an airplane that should have
machined reveals made from only 6061
aluminum.
We agree that the unsafe condition
should be clarified for the reason
provided. We have changed the wording
for the unsafe condition identified in
the SUMMARY section and in paragraph
(e) of this final rule to specify that ‘‘This
new AD was prompted by a report of a
cracked reveal made from a casting
found within a group of airplanes that
should have machined reveals made
only from 6061 aluminum.’’ We have
also clarified the Discussion section of
this final rule to specify that the NPRM
(78 FR 26720, May 8, 2013) was
prompted by that report.
Request To Revise Wording in the
NPRM (78 FR 26720, May 8, 2013)
Boeing requested numerous changes
related to the wording in paragraphs (g),
(h), (j), (u) and (v) of the NPRM (78 FR
26720, May 8, 2013).
We acknowledge the commenter’s
concerns for clarity. However, as stated
previously, this AD does not supersede
AD 2008–18–07, Amendment 39–15664
(73 FR 56960, October 1, 2008). The
changes requested by the commenter
referred to the ‘‘retained’’ paragraphs of
AD 2008–18–07, which are not restated
in this AD; therefore, no action is
necessary in this regard.
Request To Revise Service Information
Delta Airlines (Delta) requested that
Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, be revised prior to
the issuance of this final rule. Delta
stated that paragraphs (r) and (s) of the
proposed AD (78 FR 26720, May 8,
2013) (redesignated as paragraphs (i)
and (h) of this AD) are clear and
understandable; however, when Delta
reviewed the required actions in Table
1 of Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, Delta was not able
to clearly determine which conditions
were linked with which actions. Delta
stated that Boeing also agrees that the
compliance tables of Boeing Special
Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, should be clarified for operators’
use.
We disagree with delaying this AD to
wait for revised service information in
light of the urgency of the identified
unsafe condition. As Delta stated, the
tables contained in Boeing Special
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Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, are complicated and could be
misinterpreted; however, we have
addressed this concern by specifying the
requirements and clarifying the
appropriate actions in paragraphs (h)
and (i) of this AD. When the service
information is revised, we might
consider approving it as an alternative
method of compliance (AMOC) for these
actions. We have not changed this final
rule in this regard.
Request To Address an Error in Service
Information
Delta stated that, in the last row under
the ‘‘Action’’ column of Table 8 of
paragraph 1.E., Compliance, of Boeing
Special Attention Service Bulletin 747–
53–2460, Revision 2, dated December
22, 2010, there is a reference to ‘‘Table
9,’’ which does not exist. Delta stated
that the correct paragraph reference is
‘‘Paragraph 3.B., Part 2,’’ as confirmed
in Delta’s correspondence with Boeing.
Delta requested that Boeing Special
Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, be revised prior to the issuance of
this final rule, or that we address this
error in this final rule, or, at a
minimum, address this error in a global
AMOC.
We partially agree. We disagree to
wait for revised service information in
light of the urgency of the identified
unsafe condition. However, we agree
that the reference to Table 9 in
paragraph 1.E., Compliance, of Boeing
Special Attention Service Bulletin 747–
53–2460, Revision 2, dated December
22, 2010, is incorrect. To address this
error, we have added a new paragraph
(m) in this AD to state that, where the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–
53–2460, Revision 2, dated December
22, 2010, specify a post-repair detailed
inspection in accordance with Table 9,
this AD requires a detailed inspection in
accordance with paragraph 3.B., Part 2,
of the Accomplishment Instructions of
Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010. When revised
service information becomes available,
we might consider approving it as an
AMOC for the actions required by this
AD.
Request To Revise the Proposed AD To
Include an Inspection for a Sharp Edge
for Group 4 Airplanes
Boeing asked that we revise paragraph
(r)(2) of the proposed AD (78 FR 26720,
May 8, 2013) (redesignated as paragraph
(i)(2) of this AD) to include an
inspection for a potential sharp edge
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common to the reveal. Boeing stated
that this inspection might be the first
inspection performed and, therefore, it
is possible that a sharp edge could be
found on a machined reveal.
We do not agree to revise the wording
of paragraph (i)(2) of this AD
(designated as paragraph (r)(2) of the
proposed AD (78 FR 26720, May 8,
2013)). Paragraph (i)(2) of this AD
requires, for previously inspected Group
4 airplanes, a material-type inspection
to determine if the corner reveal is a
casting, and, if a casting is found,
continued inspections or replacement of
the reveal with a two-piece machined
reveal. Castings do not have sharp
edges. Group 4 airplanes that were not
previously inspected or changed, that
have corner reveals found not to be
castings, require inspections for a sharp
edge in paragraph (g)(2) of this AD. We
have not changed this final rule in this
regard.
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Request for Alternative Corrective
Action for Group 4 Airplanes
Boeing asked that we revise paragraph
(t)(1) of the proposed AD (78 FR 26720,
May 8, 2013) (redesignated as paragraph
(g)(1) of this AD) to allow a weld repair
for a cracked reveal made from a casting
on Group 4 airplanes. Boeing stated that
this would allow operators to repair the
casting if they cannot obtain a machined
reveal.
We agree that paragraph (g)(1) of this
AD should allow a weld repair as an
alternative corrective action since this
was a permitted action for Group 2
airplanes in AD 2008–18–07,
Amendment 39–15664 (73 FR 56960,
October 1, 2008). This alternative
corrective action for Group 4 airplanes
was contained in Boeing Special
Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, but was inadvertently omitted in
the proposed AD (78 FR 26720, May 8,
2013). Paragraph (t) of the NPRM is
redesignated as paragraph (g) in this AD
and we have revised paragraph (g)(1) by
adding new paragraphs (g)(1)(i) and
(g)(1)(ii) in order to allow a weld repair
as an option to replacing the reveal if
any cracking is found. In paragraph
(g)(1)(ii) of this AD we specify repairing
in accordance with Part 4 of Boeing
Special Attention Service Bulletin 747–
53–2460, Revision 2, dated December
22, 2010. The inspection for cracking
specified in paragraph (g)(1) of this AD
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is to be repeated thereafter at intervals
not to exceed 3,000 flight cycles until a
new two-piece reveal is installed in
accordance with the requirements of
paragraph (g)(1)(i) of this AD.
Request To Reference Service Bulletin
Information Notices or Revise Service
Bulletin
Delta requested that Boeing Service
Bulletin Information Notice 747–53–
2460 IN 03, dated March 24, 2011, be
referenced as an approved deviation
from Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010. Alternatively,
Boeing requested that we delay the
issuance of this final rule until Boeing
revises Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, to incorporate the
changes outlined in that information
notice.
We partially agree. We agree that
Boeing Service Bulletin Information
Notice 747–53–2460 IN 03, dated March
24, 2011, contains acceptable
information for the inspection and
modification mandated in this AD.
However, we disagree with delaying
issuance of this final rule until revised
service information becomes available.
We have determined that to delay this
final rule would be inappropriate,
because the inspections of the number
3 MED reveals and corrective actions are
needed to reduce the risk of the
identified unsafe condition addressed in
this AD. The information that Boeing
Service Bulletin Information Notice
747–53–2460 IN 03, dated March 24,
2011, clarifies is for reference only and
is not required to address the identified
unsafe condition. When revised service
information becomes available, we
might consider approving it as an
AMOC for the actions required by this
AD. We have made no change to this AD
in this regard.
Explanation of Additional Changes
Made to This Final Rule
We redesignated paragraphs (r) and
(r)(2) of the NPRM (78 FR 26720, May
8, 2013) as paragraphs (i) and (i)(2) of
this final rule and removed the phrase
‘‘Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010,’’ from the initial
compliance times listed in those
paragraphs. In the proposed AD, we
stated that the compliance times could
be calculated from the most recent work
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77381
performed in accordance with Boeing
Special Attention Service Bulletin 747–
53–2460, Revision 1, dated February 13,
2007; or Revision 2, dated December 22,
2010; but this would introduce an error
in paragraph (i) of this AD since it
would require operators to complete the
inspections required by Boeing Special
Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, for a second time, if the reference
to Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, remained.
Paragraph (i)(1) of this final rule
specifies inspections for cracking of any
corner reveal found to be a one-piece or
two-piece casting. Boeing Special
Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22,
2010, provides inspection procedures
for one-piece corner reveals, but not for
the two-piece corner reveals. Because
the inspection procedures for the twopiece corner reveals were not included
in the service information, operators
would have been unable to comply with
the proposed requirement to inspect a
two-piece corner reveal, and in this case
would have been required to obtain
approval of an alternative method of
compliance for this inspection. We have
therefore revised paragraph (i)(1) of this
AD to provide the appropriate
procedures for both scenarios.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM (78 FR
26720, May 8, 2013) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM (78 FR 26720,
May 8, 2013).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 166
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
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ESTIMATED COSTS
Action
Material type inspection and
inspection for cracks.
Labor cost
Parts cost
Cost per product
14 work-hours × $85 per hour
= $1,190 per inspection
cycle.
$0
$1,190 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 inspections. We have no way of
Cost on U.S. operators
$197,540 per inspection
cycle.
determining the number of aircraft that
might need these actions:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Corner reveal removal and replacement
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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(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.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2014–24–05 The Boeing Company:
Amendment 39–18038; Docket No.
FAA–2013–0366; Directorate Identifier
2011–NM–024–AD.
(a) Effective Date
This AD is effective January 28, 2015.
(b) Affected ADs
Certain requirements of this AD terminate
certain requirements of 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, identified as
Group 4 airplanes in Boeing Special
Attention Service Bulletin 747–53–2460,
Revision 2, dated December 22, 2010, except
airplanes that have been converted to an allcargo configuration. Also, the requirements
of this AD are applicable when a converted
airplane operating in an all-cargo
configuration is converted back to a
passenger or passenger/cargo configuration.
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Cost per product
$10,970 per inspection cycle.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by a report of a
cracked reveal made from a casting found
within a group of airplanes that should only
have machined reveals made from 6061
aluminum. We are issuing 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) 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 AD 2008–18–07,
Amendment 38–15664 (73 FR 56960, October
1, 2008), for that airplane only.
(1) If, during any inspection required by
paragraph (g) of this AD, any corner reveal
is found to be a casting: Before the
accumulation of 7,000 total flight cycles;
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
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number 3 MED corner reveal was done in
accordance with Boeing Service Bulletin
747–53A2378, Revision 4, dated June 10,
2010; whichever occurs later; 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 a new two-piece reveal is installed in
accordance with the requirements of
paragraph (g)(1)(i) of this AD. If any cracking
is found, do the actions specified in
paragraph (g)(1)(i) or (g)(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 (g) 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
two-piece corner reveal in accordance with
the requirements of paragraph (j) of this AD.
(i) If any sharp edge is found during any
inspection required by paragraph (g)(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 (g)(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.
(h) 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
VerDate Sep<11>2014
16:05 Dec 23, 2014
Jkt 235001
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 (j) of this AD.
If any cracking is found during any
inspection required by this paragraph, before
further flight, replace the one-piece 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.
(i) 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; 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
within 1,000 flight cycles after the effective
date of this AD; whichever occurs later; do
a material type inspection to determine if the
corner reveal is a casting, in accordance with
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 AD 2008–18–07,
Amendment 39–15664 (73 FR 56960, October
1, 2008), for these airplanes.
(1) If, during any inspection required by
paragraph (i) 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. For one-piece reveals, inspect
in accordance with Part 2 of the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22, 2010;
for two-piece reveals, inspect using a method
approved in accordance with the procedures
specified in paragraph (n) of this AD. Repeat
the inspection thereafter at intervals not to
exceed 3,000 flight cycles until a new twopiece reveal is installed in accordance with
the requirements of paragraph (i)(1)(i) of this
AD. If any cracking is found, do the actions
specified in paragraph (i)(1)(i) or (i)(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
PO 00000
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Fmt 4700
Sfmt 4700
77383
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 (i) 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; 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 this
paragraph, 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.
(j) 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 (g), (h),
and (i) of this AD.
(k) Parts Installation Prohibition: (Cast 356
Aluminum) Reveals
As of the effective date of this AD, no
person may install a door lower forward
corner reveal made of cast 356 aluminum on
any airplane at a location specified in the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22, 2010.
This parts installation prohibition ends the
parts installation prohibition specified in
paragraph (n) of AD 2008–18–07,
Amendment 39–15664 (73 FR 56960, October
1, 2008), for the airplanes identified in
paragraph (c) of this AD.
(l) Parts Installation Limitation: (Machined
6061 Aluminum) Reveals
As of the effective date of this AD, no
person may install a door lower forward
corner reveal made of machined 6061
aluminum on any airplane at a location
specified in the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 747–53–2460, Revision 2,
dated December 22, 2010, unless it has been
confirmed/reworked to be without a sharp
edge, in accordance with Part 1 of the
Accomplishment Instructions of Boeing
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Special Attention Service Bulletin 747–53–
2460, Revision 2, dated December 22, 2010.
This parts installation prohibition ends the
parts installation prohibition specified in
paragraph (o) of AD 2008–18–07,
Amendment 39–15664 (73 FR 56960, October
1, 2008), for the airplanes identified in
paragraph (c) of this AD.
(m) Exceptions to Service Information
Specifications
Where Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010, specifies a post-repair
detailed inspection in accordance with Table
9, this AD requires a detailed inspection in
accordance with paragraph 3.B., Part 2, of
Boeing Special Attention Service Bulletin
747–53–2460, Revision 2, dated December
22, 2010.
(n) 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
paragraph (o) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCREQUESTS@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.
mstockstill on DSK4VPTVN1PROD with RULES
(o) Related Information
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.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service
Bulletin 747–53–2460, Revision 2, dated
December 22, 2010.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
VerDate Sep<11>2014
16:05 Dec 23, 2014
Jkt 235001
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com.
(4) You may view this service information
at 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.
5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Document Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
[FR Doc. 2014–30132 Filed 12–23–14; 8:45 am]
JoAnn Theriault, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
phone: 781–238–7105; fax: 781–238–
7199; email: jo-ann.theriault@faa.gov.
BILLING CODE 4910–13–P
SUPPLEMENTARY INFORMATION:
Issued in Renton, Washington, on
November 19, 2014.
Suzanne Masterson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0072; Directorate
Identifier 2013–NE–04–AD; Amendment 39–
18017; AD 2014–23–01]
RIN 2120–AA64
Airworthiness Directives; Pratt &
Whitney Division Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; correction.
AGENCY:
The FAA is correcting an
airworthiness directive (AD) that
published in the Federal Register. That
AD applies to all Pratt & Whitney
Division (PW) PW4074, PW4074D,
PW4077, PW4077D, PW4084D,
PW4090, and PW4090–3 turbofan
engine models with certain second-stage
high-pressure turbine (HPT) air seals
installed. The time required to perform
the initial eddy current inspection (ECI)
in the Compliance section is incorrect.
This document corrects that error. In all
other respects, the original document
remains the same.
DATES: This final rule is effective on
December 26, 2014. The effective date of
AD 2014–23–01, Amendment 39–18017
(79 FR 69369, November 21, 2014)
remains December 26, 2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 17, 2013 (78 FR 49111,
August 13, 2013).
ADDRESSES: You may examine the AD
docket on the Internet at https://
SUMMARY:
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
FOR FURTHER INFORMATION CONTACT:
AD 2014–
23–01, Amendment 39–18017 (79 FR
69369, November 21, 2014), requires
initial and repetitive inspections for
cracks in second-stage HPT air seals, the
removal of the mating hardware if the
second-stage HPT air seal is found with
a through-crack, and a mandatory
terminating action for all PW PW4074,
PW4074D, PW4077, PW4077D,
PW4084D, PW4090, and PW4090–3
turbofan engine models with certain
second-stage HPT air seals installed.
As published, the time required to
perform the initial ECI in the
Compliance section is incorrect. AD
2014–23–01, paragraph (e)(2)(i), requires
an initial ECI for cracks within 1,000
cycles-in-service after September 17,
2013, or before further flight, whichever
occurs later. That compliance time is
more restrictive than intended and will
likely ground airplanes. The intent was
to require an initial ECI for cracks before
reaching 2,200 cycles since new, or
within 1,000 cycles-in-service after
September 17, 2013, or before further
flight, whichever occurs later.
No other part of the preamble or
regulatory information has been
changed.
The effective date of AD 2014–23–01
remains December 26, 2014.
Correction of Regulatory Text
§ 39.13
[Corrected]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–15–09, Amendment 39–17525 (78
FR 49111, August 13, 2013), and adding
the following new AD:
■
2014–23–01 Pratt & Whitney Division:
Amendment 39–18017; Docket No.
FAA–2013–0072; Directorate Identifier
2013–NE–04–AD.
E:\FR\FM\24DER1.SGM
24DER1
]]>Agencies
[Federal Register Volume 79, Number 247 (Wednesday, December 24, 2014)]
[Rules and Regulations]
[Pages 77379-77384]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-30132]
[[Page 77379]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0366; Directorate Identifier 2011-NM-024-AD;
Amendment 39-18038; AD 2014-24-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) 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. This
AD was prompted by a report of a cracked reveal made from a casting
found within a group of airplanes that should have machined reveals
made only from 6061 aluminum. This AD requires an inspection to
determine the material of the number 3 main entry door (MED) corner
reveal, repetitive inspections of certain reveals for cracking, and
corrective action if necessary. This AD also requires repetitive
inspections for cracking of 6061 machined aluminum one-piece corner
reveals, and replacement with 6061 machined aluminum two-piece corner
reveals if necessary, which terminates certain repetitive inspections.
We are issuing 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: This AD is effective January 28, 2015.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 28,
2015.
ADDRESSES: For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.You may view this 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0366; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: 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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2008-18-07, Amendment 39-15664 (73 FR 56960,
October 1, 2008). AD 2008-18-07 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 NPRM published in
the Federal Register on May 8, 2013 (78 FR 26720). The NPRM was
prompted by a report of a cracked reveal made from a casting found
within a group of airplanes that should have machined reveals made only
from 6061 aluminum. The NPRM proposed to retain all the requirements of
AD 2008-18-07. The NPRM also proposed to add, for certain airplanes, an
inspection to determine the material of the number 3 MED corner reveal,
repetitive inspections for cracking of 6061 machined aluminum one-piece
corner reveals, and replacement with 6061 machined aluminum two-piece
corner reveals if necessary, which terminates certain repetitive
inspections. We are issuing 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.
Related AD
AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008),
requires, for 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, an inspection to determine the material of a number 3 MED
corner 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. AD 2008-18-07 allows reveal
replacement as an option to certain inspections. AD 2008-18-07 was
prompted by reports of cracking and/or a sharp edge in the lower
forward corner reveal of the number 3 MEDs. AD 2008-18-07 refers 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 specified in that AD.
Explanation of Difference in Requirements Between the NPRM (78 FR
26720, May 8, 2013) and This Final Rule
In the NPRM (78 FR 26720, May 8, 2013), the FAA proposed to
supersede AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October 1,
2008), to reflect the changes in airplane groups specified in revised
service information, Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010. However, based on the
comments received on the NPRM, it became evident that it was difficult
to follow the numerous changes between 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, as well as in following the corresponding actions
specified in the NPRM.
There are only two significant changes in Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010: (1)
Airplanes having line numbers 1038 through 1270 were moved from Group 2
to Group 4; and (2) for Group 4 airplanes, there are additional
actions. Therefore, for clarity, we have determined that a less
burdensome approach is to revise this final rule to include only the
new actions for Group 4 airplanes. Instead of superseding AD 2008-18-
07, Amendment 39-15664 (73 FR 56960, October 1, 2008), this final rule
is a stand-alone AD, applicable
[[Page 77380]]
only to Group 4 airplanes as identified in Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010,
except for those airplanes that have been converted to an all-cargo
configuration. Airplanes identified in the applicability of AD 2008-18-
07 are still required to continue to comply with the requirements of
that AD.
Since this AD does not supersede AD 2008-18-07, Amendment 39-15664
(73 FR 56960, October 1, 2008), paragraphs (g) through (m), (p), (q),
and (v) of the NPRM (78 FR 26720, May 8, 2013) are not included in this
AD. Also, the corresponding paragraph identifiers have been
redesignated in this final rule, as listed in the following table:
Redesignated Paragraph Identifiers
------------------------------------------------------------------------
Requirement in the proposed AD (78
FR 26720, May 8, 2013) Corresponding requirement in this AD
------------------------------------------------------------------------
paragraph (t) paragraph (g).
paragraph (s) paragraph (h).
paragraph (r) paragraph (i).
paragraph (u) paragraph (j).
paragraph (n) paragraph (k).
paragraph (o) paragraph (l).
paragraph (w) paragraph (n).
------------------------------------------------------------------------
We have also revised paragraphs (n) and (o) of the proposed AD (78
FR 26720, May 8, 2013) (redesignated as paragraphs (k) and (l) of this
AD) that referred to ``AD 2008-18-07.'' In paragraphs (k) and (l) of
this AD, we have referred to the current service information, Boeing
Special Attention Service Bulletin 747-53-2460, Revision 2, dated
December 22, 2010, instead of AD 2008-18-07, Amendment 39-15664 (73 FR
56960, October 1, 2008), for the locations where cast 356 aluminum
reveals and machined 6061 aluminum reveals may not be installed.
Paragraphs (k) and (l) of this AD state that the parts installation
prohibition ends the parts installation prohibitions specified in
paragraphs (n) and (o) of AD 2008-18-07, Amendment 39-15664 (73 FR
56960, October 1, 2008).
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM (78
FR 26720, May 8, 2013) and the FAA's response to each comment.
Request To Clarify the Cause of the Unsafe Condition
Boeing asked that we clarify the cause of the unsafe condition
identified in paragraph (e) of the proposed AD (78 FR 26720, May 8,
2013). Boeing stated that the report that prompted the proposed
supersedure of AD 2008-18-07, Amendment 39-15664 (73 FR 56960, October
1, 2008), involved a cracked casting on an airplane that should have
machined reveals made from only 6061 aluminum.
We agree that the unsafe condition should be clarified for the
reason provided. We have changed the wording for the unsafe condition
identified in the SUMMARY section and in paragraph (e) of this final
rule to specify that ``This new AD was prompted by a report of a
cracked reveal made from a casting found within a group of airplanes
that should have machined reveals made only from 6061 aluminum.'' We
have also clarified the Discussion section of this final rule to
specify that the NPRM (78 FR 26720, May 8, 2013) was prompted by that
report.
Request To Revise Wording in the NPRM (78 FR 26720, May 8, 2013)
Boeing requested numerous changes related to the wording in
paragraphs (g), (h), (j), (u) and (v) of the NPRM (78 FR 26720, May 8,
2013).
We acknowledge the commenter's concerns for clarity. However, as
stated previously, this AD does not supersede AD 2008-18-07, Amendment
39-15664 (73 FR 56960, October 1, 2008). The changes requested by the
commenter referred to the ``retained'' paragraphs of AD 2008-18-07,
which are not restated in this AD; therefore, no action is necessary in
this regard.
Request To Revise Service Information
Delta Airlines (Delta) requested that Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, be
revised prior to the issuance of this final rule. Delta stated that
paragraphs (r) and (s) of the proposed AD (78 FR 26720, May 8, 2013)
(redesignated as paragraphs (i) and (h) of this AD) are clear and
understandable; however, when Delta reviewed the required actions in
Table 1 of Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010, Delta was not able to clearly
determine which conditions were linked with which actions. Delta stated
that Boeing also agrees that the compliance tables of Boeing Special
Attention Service Bulletin 747-53-2460, Revision 2, dated December 22,
2010, should be clarified for operators' use.
We disagree with delaying this AD to wait for revised service
information in light of the urgency of the identified unsafe condition.
As Delta stated, the tables contained in Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010, are
complicated and could be misinterpreted; however, we have addressed
this concern by specifying the requirements and clarifying the
appropriate actions in paragraphs (h) and (i) of this AD. When the
service information is revised, we might consider approving it as an
alternative method of compliance (AMOC) for these actions. We have not
changed this final rule in this regard.
Request To Address an Error in Service Information
Delta stated that, in the last row under the ``Action'' column of
Table 8 of paragraph 1.E., Compliance, of Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010,
there is a reference to ``Table 9,'' which does not exist. Delta stated
that the correct paragraph reference is ``Paragraph 3.B., Part 2,'' as
confirmed in Delta's correspondence with Boeing. Delta requested that
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2,
dated December 22, 2010, be revised prior to the issuance of this final
rule, or that we address this error in this final rule, or, at a
minimum, address this error in a global AMOC.
We partially agree. We disagree to wait for revised service
information in light of the urgency of the identified unsafe condition.
However, we agree that the reference to Table 9 in paragraph 1.E.,
Compliance, of Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010, is incorrect. To address this
error, we have added a new paragraph (m) in this AD to state that,
where the Accomplishment Instructions of Boeing Special Attention
Service Bulletin 747-53-2460, Revision 2, dated December 22, 2010,
specify a post-repair detailed inspection in accordance with Table 9,
this AD requires a detailed inspection in accordance with paragraph
3.B., Part 2, of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 747-53-2460, Revision 2, dated December 22,
2010. When revised service information becomes available, we might
consider approving it as an AMOC for the actions required by this AD.
Request To Revise the Proposed AD To Include an Inspection for a Sharp
Edge for Group 4 Airplanes
Boeing asked that we revise paragraph (r)(2) of the proposed AD (78
FR 26720, May 8, 2013) (redesignated as paragraph (i)(2) of this AD) to
include an inspection for a potential sharp edge
[[Page 77381]]
common to the reveal. Boeing stated that this inspection might be the
first inspection performed and, therefore, it is possible that a sharp
edge could be found on a machined reveal.
We do not agree to revise the wording of paragraph (i)(2) of this
AD (designated as paragraph (r)(2) of the proposed AD (78 FR 26720, May
8, 2013)). Paragraph (i)(2) of this AD requires, for previously
inspected Group 4 airplanes, a material-type inspection to determine if
the corner reveal is a casting, and, if a casting is found, continued
inspections or replacement of the reveal with a two-piece machined
reveal. Castings do not have sharp edges. Group 4 airplanes that were
not previously inspected or changed, that have corner reveals found not
to be castings, require inspections for a sharp edge in paragraph
(g)(2) of this AD. We have not changed this final rule in this regard.
Request for Alternative Corrective Action for Group 4 Airplanes
Boeing asked that we revise paragraph (t)(1) of the proposed AD (78
FR 26720, May 8, 2013) (redesignated as paragraph (g)(1) of this AD) to
allow a weld repair for a cracked reveal made from a casting on Group 4
airplanes. Boeing stated that this would allow operators to repair the
casting if they cannot obtain a machined reveal.
We agree that paragraph (g)(1) of this AD should allow a weld
repair as an alternative corrective action since this was a permitted
action for Group 2 airplanes in AD 2008-18-07, Amendment 39-15664 (73
FR 56960, October 1, 2008). This alternative corrective action for
Group 4 airplanes was contained in Boeing Special Attention Service
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, but was
inadvertently omitted in the proposed AD (78 FR 26720, May 8, 2013).
Paragraph (t) of the NPRM is redesignated as paragraph (g) in this AD
and we have revised paragraph (g)(1) by adding new paragraphs (g)(1)(i)
and (g)(1)(ii) in order to allow a weld repair as an option to
replacing the reveal if any cracking is found. In paragraph (g)(1)(ii)
of this AD we specify repairing in accordance with Part 4 of Boeing
Special Attention Service Bulletin 747-53-2460, Revision 2, dated
December 22, 2010. The inspection for cracking specified in paragraph
(g)(1) of this AD is to be repeated thereafter at intervals not to
exceed 3,000 flight cycles until a new two-piece reveal is installed in
accordance with the requirements of paragraph (g)(1)(i) of this AD.
Request To Reference Service Bulletin Information Notices or Revise
Service Bulletin
Delta requested that Boeing Service Bulletin Information Notice
747-53-2460 IN 03, dated March 24, 2011, be referenced as an approved
deviation from Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010. Alternatively, Boeing requested
that we delay the issuance of this final rule until Boeing revises
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2,
dated December 22, 2010, to incorporate the changes outlined in that
information notice.
We partially agree. We agree that Boeing Service Bulletin
Information Notice 747-53-2460 IN 03, dated March 24, 2011, contains
acceptable information for the inspection and modification mandated in
this AD. However, we disagree with delaying issuance of this final rule
until revised service information becomes available. We have determined
that to delay this final rule would be inappropriate, because the
inspections of the number 3 MED reveals and corrective actions are
needed to reduce the risk of the identified unsafe condition addressed
in this AD. The information that Boeing Service Bulletin Information
Notice 747-53-2460 IN 03, dated March 24, 2011, clarifies is for
reference only and is not required to address the identified unsafe
condition. When revised service information becomes available, we might
consider approving it as an AMOC for the actions required by this AD.
We have made no change to this AD in this regard.
Explanation of Additional Changes Made to This Final Rule
We redesignated paragraphs (r) and (r)(2) of the NPRM (78 FR 26720,
May 8, 2013) as paragraphs (i) and (i)(2) of this final rule and
removed the phrase ``Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010,'' from the initial
compliance times listed in those paragraphs. In the proposed AD, we
stated that the compliance times could be calculated from the most
recent work performed in accordance with Boeing Special Attention
Service Bulletin 747-53-2460, Revision 1, dated February 13, 2007; or
Revision 2, dated December 22, 2010; but this would introduce an error
in paragraph (i) of this AD since it would require operators to
complete the inspections required by Boeing Special Attention Service
Bulletin 747-53-2460, Revision 2, dated December 22, 2010, for a second
time, if the reference to Boeing Special Attention Service Bulletin
747-53-2460, Revision 2, dated December 22, 2010, remained.
Paragraph (i)(1) of this final rule specifies inspections for
cracking of any corner reveal found to be a one-piece or two-piece
casting. Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010, provides inspection procedures for
one-piece corner reveals, but not for the two-piece corner reveals.
Because the inspection procedures for the two-piece corner reveals were
not included in the service information, operators would have been
unable to comply with the proposed requirement to inspect a two-piece
corner reveal, and in this case would have been required to obtain
approval of an alternative method of compliance for this inspection. We
have therefore revised paragraph (i)(1) of this AD to provide the
appropriate procedures for both scenarios.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM (78 FR 26720, May 8, 2013) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the NPRM (78 FR 26720, May 8, 2013).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 166 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
[[Page 77382]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Material type inspection and 14 work-hours x $85 $0 $1,190 per $197,540 per
inspection for cracks. per hour = $1,190 inspection cycle. inspection cycle.
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 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
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(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.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2014-24-05 The Boeing Company: Amendment 39-18038; Docket No. FAA-
2013-0366; Directorate Identifier 2011-NM-024-AD.
(a) Effective Date
This AD is effective January 28, 2015.
(b) Affected ADs
Certain requirements of this AD terminate certain requirements
of 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, identified as
Group 4 airplanes 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. Also, the
requirements of this AD are applicable 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 cracked reveal made from a
casting found within a group of airplanes that should only have
machined reveals made from 6061 aluminum. We are issuing 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) 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 AD 2008-18-
07, Amendment 38-15664 (73 FR 56960, October 1, 2008), for that
airplane only.
(1) If, during any inspection required by paragraph (g) of this
AD, any corner reveal is found to be a casting: Before the
accumulation of 7,000 total flight cycles; 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
[[Page 77383]]
number 3 MED corner reveal was done in accordance with Boeing
Service Bulletin 747-53A2378, Revision 4, dated June 10, 2010;
whichever occurs later; 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 a new two-piece reveal is installed in accordance with the
requirements of paragraph (g)(1)(i) of this AD. If any cracking is
found, do the actions specified in paragraph (g)(1)(i) or (g)(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 (g) 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 two-piece
corner reveal in accordance with the requirements of paragraph (j)
of this AD.
(i) If any sharp edge is found during any inspection required by
paragraph (g)(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 (g)(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.
(h) 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 (j) of this AD. If any cracking is found
during any inspection required by this paragraph, 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.
(i) 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; 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 within 1,000 flight cycles after the effective date of
this AD; whichever occurs later; do a material type inspection to
determine if the corner reveal is a casting, in accordance with 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 AD 2008-18-07, Amendment 39-15664 (73
FR 56960, October 1, 2008), for these airplanes.
(1) If, during any inspection required by paragraph (i) 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.
For one-piece reveals, inspect in accordance with Part 2 of the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 747-53-2460, Revision 2, dated December 22, 2010; for two-
piece reveals, inspect using a method approved in accordance with
the procedures specified in paragraph (n) of this AD. Repeat the
inspection thereafter at intervals not to exceed 3,000 flight cycles
until a new two-piece reveal is installed in accordance with the
requirements of paragraph (i)(1)(i) of this AD. If any cracking is
found, do the actions specified in paragraph (i)(1)(i) or (i)(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 (i) 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; 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 this
paragraph, 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.
(j) 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 (g), (h), and (i) of this AD.
(k) Parts Installation Prohibition: (Cast 356 Aluminum) Reveals
As of the effective date of this AD, no person may install a
door lower forward corner reveal made of cast 356 aluminum on any
airplane at a location specified in the Accomplishment Instructions
of Boeing Special Attention Service Bulletin 747-53-2460, Revision
2, dated December 22, 2010. This parts installation prohibition ends
the parts installation prohibition specified in paragraph (n) of AD
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), for
the airplanes identified in paragraph (c) of this AD.
(l) Parts Installation Limitation: (Machined 6061 Aluminum) Reveals
As of the effective date of this AD, no person may install a
door lower forward corner reveal made of machined 6061 aluminum on
any airplane at a location specified in the Accomplishment
Instructions of Boeing Special Attention Service Bulletin 747-53-
2460, Revision 2, dated December 22, 2010, unless it has been
confirmed/reworked to be without a sharp edge, in accordance with
Part 1 of the Accomplishment Instructions of Boeing
[[Page 77384]]
Special Attention Service Bulletin 747-53-2460, Revision 2, dated
December 22, 2010. This parts installation prohibition ends the
parts installation prohibition specified in paragraph (o) of AD
2008-18-07, Amendment 39-15664 (73 FR 56960, October 1, 2008), for
the airplanes identified in paragraph (c) of this AD.
(m) Exceptions to Service Information Specifications
Where Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010, specifies a post-repair
detailed inspection in accordance with Table 9, this AD requires a
detailed inspection in accordance with paragraph 3.B., Part 2, of
Boeing Special Attention Service Bulletin 747-53-2460, Revision 2,
dated December 22, 2010.
(n) 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 paragraph (o) 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.
(o) Related Information
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.
(p) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Special Attention Service Bulletin 747-53-2460,
Revision 2, dated December 22, 2010.
(ii) Reserved.
(3) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
(4) You may view this service information at 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.
5) You may view this service information that is incorporated by
reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on November 19, 2014.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-30132 Filed 12-23-14; 8:45 am]
BILLING CODE 4910-13-P
