Airworthiness Directives; The Boeing Company Airplanes, 14707-14711 [2016-06001]
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Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations
1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service
Bulletin 72–0309 R00, dated March 11, 2016,
unless at least one engine has been reworked
in accordance with paragraph 3.A.(1)(b), 3.B.,
or 3.C. of the Accomplishment Instructions of
GE GEnx–1B Service Bulletin 72–0309 R00,
dated March 11, 2016.
(k) Reporting Provisions
Although GE GEnx Service Bulletin GEnx–
1B 72–0309 R00, dated March 11, 2016,
specifies reporting certain tip clearance
measurements to GE, this AD does not
require any report.
(l) 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 (m) 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,
modification, or alteration 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. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
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(m) Related Information
For more information about this AD,
contact Sue Lucier, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6438; fax: 425–
917–6590; email: Suzanne.Lucier@faa.gov.
(n) 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) GE GEnx–1B Service Bulletin 72–0309
R00, dated March 11, 2016.
(ii) Reserved.
(3) For service information identified in
this AD, contact General Electric Company,
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513–552–3272;
email: geae.aoc@ge.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
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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.
Issued in Renton, Washington, on March
14, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–06117 Filed 3–17–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0774; Directorate
Identifier 2013–NM–154–AD; Amendment
39–18438; AD 2016–06–07]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2006–22–
15 for all The Boeing Company Model
747–100, 747–100B, 747–100B SUD,
747–200B, 747–200C, 747–200F, 747–
300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes. AD
2006–22–15 required repetitive
inspections for cracking of certain panel
webs and stiffeners of the nose wheel
well (NWW), and corrective actions if
necessary; and replacement of certain
panels with new panels, which
terminates the repetitive inspections.
This new AD reduces a compliance time
and adds certain inspections and an
applicable repair. This AD was
prompted by multiple reports of fatigue
cracking in the NWW top panel and side
panel webs and stiffeners. We are
issuing this AD to prevent fatigue
cracking of the NWW side and top
panels, which could result in a NWW
depressurization event severe enough to
reduce the structural integrity of the
fuselage.
SUMMARY:
This AD is effective April 22,
2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 22, 2016.
DATES:
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14707
For service information
identified in this final rule, 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0774.
ADDRESSES:
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–2014–
0774; 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 supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2006–22–15, Amendment 39–14812 (71
FR 64884, November 6, 2006) (‘‘AD
2006–22–15’’). AD 2006–22–15 applied
to all The Boeing Company Model 747–
100, 747–100B, 747–100B SUD, 747–
200B, 747–200C, 747–200F, 747–300,
747–400, 747–400D, 747–400F, 747SR,
and 747SP series airplanes. The SNPRM
published in the Federal Register on
September 18, 2015 (80 FR 56407) (‘‘the
SNPRM’’). We preceded the SNPRM
with a notice of proposed rulemaking
(NPRM) that published in the Federal
Register on November 17, 2014 (79 FR
68388) (‘‘the NPRM’’). The NPRM
proposed to continue to require
repetitive inspections for cracking of
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certain panel webs and stiffeners of the
NWW, and corrective actions if
necessary; and replacement of certain
panels with new panels, which
terminates the repetitive inspections.
The NPRM proposed to reduce a
compliance time and add certain
inspections and repair if necessary. The
NPRM was prompted by reports of
fatigue cracking in the panel webs and
stiffeners of the NWW found prior to the
inspection threshold of AD 2006–22–15.
The SNPRM revised the NPRM by
specifying a repetitive inspection
interval for a certain NWW area
inspection. We are issuing this AD to
prevent fatigue cracking of the NWW
side and top panels, which could result
in a NWW depressurization event severe
enough to reduce the structural integrity
of the fuselage.
approved AMOCs, if the compliance
times are acceptable according to the
SNPRM.
We agree with the commenter’s
request. We have revised paragraph
(p)(4) of this AD to state that: AMOC
actions approved previously for AD
2006–22–15 are approved as AMOCs for
the corresponding actions of this AD. In
addition, paragraph (p)(4) of this AD
states that the compliance times in
AMOCs approved previously for AD
2006–22–15 are not approved for the
corresponding actions and compliance
times in this AD, if this AD specifies an
earlier compliance time than that
specified in AD 2006–22–15; and that
compliance times in AMOCs approved
previously for AD 2006–22–15 that meet
the requirements of this AD are
acceptable.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM and the FAA’s
response to each comment.
Conclusion
Support for the SNPRM
Two commenters supported the
SNPRM. One commenter stated that the
FAA should continue to execute its
administrative power to ensure traveler
safety and industry compliance, adding
that while the original rule was good,
ensuring that specifics are covered and
timetables are available is an important
improvement.
Request for Credit for Compliance
Times in Previously Approved
Alternative Methods of Compliance
(AMOCs)
Boeing requested that we allow credit
for the compliance times in previously
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the change described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under
1 CFR Part 51
We reviewed the following Boeing
service bulletins.
• Boeing Alert Service Bulletin 747–
53A2808, dated November 30, 2012.
This service information describes
procedures for replacement of the side
and top panel webs, support beams, and
stiffeners of the NWW; an inspection for
cracking of the attaching structural
elements that are common to the
removed top and side panels of the
NWW; repetitive post-modification
inspections for cracks in the top and
side panel webs and stiffeners; and
repairs.
• Boeing Service Bulletin 747–
53A2465, Revision 5, dated July 11,
2013. This service information describes
procedures for doing inspections for
cracking of the NWW side panel and top
panel webs and longitudinal stiffeners
for cracks, and related investigative and
corrective actions.
• Boeing Service Bulletin 747–
53A2562, Revision 3, dated July 11,
2013. This service information describes
procedures for replacement of the side
and top panel webs and certain
stiffeners of the NWW; an inspection for
cracks in attaching structural elements
that are common to the removed top
panel and side panels; repetitive postmodification inspections for cracks in
the top and side panel webs and
stiffeners; and repairs.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD will affect
255 airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
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Inspections [actions retained from AD 2006–
22–15].
Modification [actions retained from AD 2006–
22–15].
Post-modification Inspections [new action].
Labor cost
119 work-hours × $85 per
hour = $10,115 per inspection cycle.
Up to 1,346 work-hours ×
$85 per hour =
$114,410.
119 work-hours × $85 per
hour = $10,115 per inspection cycle.
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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Cost per
product
Parts cost
$0 ......................................
$10,115 per inspection
cycle.
$2,579,325 per inspection
cycle.
Up to $144,248 .................
Up to $258,658 .................
Up to $65,957,790.
$0 ......................................
$10,115 per inspection
cycle.
$2,579,325 per 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
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operators
Frm 00020
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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
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promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(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
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
removing Airworthiness Directive (AD)
2006–22–15, Amendment 39–14812 (71
FR 64884, November 6, 2006) (‘‘AD
2006–22–15’’), and adding the following
new AD:
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■
2016–06–07 The Boeing Company:
Amendment 39–18438; Docket No.
FAA–2014–0774; Directorate Identifier
2013–NM–154–AD.
(a) Effective Date
This AD is effective April 22, 2016.
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(b) Affected ADs
This AD replaces AD 2006–22–15,
Amendment 39–14812 (71 FR 64884,
November 6, 2006) (‘‘AD 2006–22–15’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 747–100, 747–100B, 747–
100B SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–400F,
747SR, and 747SP series airplanes,
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by multiple reports
of cracking in the nose wheel well (NWW)
top panel and side panel webs and stiffeners.
We are issuing this AD to prevent fatigue
cracking of the NWW side and top panels,
which could result in a NWW
depressurization event severe enough to
reduce the structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections and Corrective
Actions With New Compliance Times
Except as specified in paragraphs (h)(1)
and (h)(2) of this AD, at the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 747–53A2465,
Revision 5, dated July 11, 2013: Do the
actions specified in paragraphs (g)(1), (g)(2),
and (g)(3) of this AD, and do all applicable
related investigative and corrective actions;
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2465, Revision 5, dated July 11, 2013,
except as specified in paragraph (h)(3) of this
AD. Do all applicable related investigative
and corrective actions before further flight.
Repeat the inspections specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2465, Revision 5,
dated July 11, 2013. The repetitive interval
for the inspection of Area 2 specified in table
1 in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2465, Revision 5,
dated July 11, 2013, is 1,000 flight cycles. In
table 2 and table 3 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2465, Revision 5, dated July 11,
2013, the date ‘‘January 27, 2005,’’ is the
effective date of AD 2004–25–23,
Amendment 39–13911 (69 FR 76839,
December 23, 2004); and the date ‘‘May 10,
2005,’’ is the effective date of AD 2005–09–
02, Amendment 39–14070 (70 FR 21141,
April 25, 2005; corrected May 25, 2005 (70
FR 29940)).
(1) Do an external detailed inspection for
cracks of the top and sidewall panel webs of
the NWW (specified as Area 1 and Area 2 in
Boeing Service Bulletin 747–53A2465,
Revision 5, dated July 11, 2013).
(2) Do internal detailed and surface high
frequency eddy current (HFEC) inspections
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for cracks of the sidewall panel and top panel
stiffeners of the NWW (specified as Area 3 in
Boeing Service Bulletin 747–53A2465,
Revision 5, dated July 11, 2013).
(3) Do an external detailed and ultrasonic
testing (UT) inspection for cracks of the top
and sidewall panel webs of the NWW
(specified as Area 1 and Area 2 in Boeing
Service Bulletin 747–53A2465, Revision 5,
dated July 11, 2013).
(h) Exceptions to Boeing Service Bulletin
747–53A2465, Revision 5, Dated July 11,
2013
(1) Table 1 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2465, Revision 5, dated July 11,
2013, applies to airplanes with less than
15,000 total flight cycles ‘‘as of the Revision
5 date of this service bulletin.’’ For this AD,
however, table 1 applies to airplanes with the
specified total flight cycles as of the effective
date of this AD.
(2) Table 1 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2465, Revision 5, dated July 11,
2013, specifies a compliance time of ‘‘13,000
total flight-cycles,’’ or ‘‘within 1,000 flight
cycles after the Revision 5 date of this service
bulletin,’’ whichever occurs later. This AD
requires compliance before the accumulation
of 10,000 total flight cycles or within 1,000
flight cycles after the effective date of this
AD, whichever occurs later.
(3) If any cracking or damage is found
during any inspection required by paragraph
(g) of this AD, and Boeing Service Bulletin
747–53A2465, Revision 5, dated July 11,
2013, specifies to contact Boeing for
appropriate action: Before further flight,
repair the cracking or damage using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD.
(i) NWW Modification
For airplanes identified in Boeing Service
Bulletin 747–53A2562, Revision 3, dated July
11, 2013: At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2562, Revision 3,
dated July 11, 2013, replace the left-side,
right-side, and top panels of the NWW, as
applicable, with new panels, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2562,
Revision 3, dated July 11, 2013. As of the
effective date of this AD, concurrently with
doing the replacement specified in Boeing
Service Bulletin 747–53A2562, Revision 3,
dated July 11, 2013, do a detailed inspection
for any cracks or damage (including, but not
limited to, dents and corrosion) in all
attaching structural elements that are
common to the removed top panel and side
panels, as applicable, and do all applicable
corrective actions, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2562, Revision 3,
dated July 11, 2013. If any crack or damage
is found, before further flight, repair the
cracking or damage using a method approved
in accordance with the procedures specified
in paragraph (p) of this AD. In paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2562, Revision 3, dated July 11,
2013, the date ‘‘December 11, 2006,’’ is the
effective date of AD 2006–22–15.
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(j) Repetitive Post-Modification Inspections
For airplanes on which the replacement
specified in paragraph (i) of this AD has been
done: Except as required by paragraph (k) of
this AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2562, Revision 3,
dated July 11, 2013, do the actions specified
in paragraphs (j)(1), (j)(2), and (j)(3) of this
AD. If any crack is found: Before further
flight, repair the cracking using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD. Repeat
the inspections specified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD thereafter at the
applicable intervals specified in paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 747–53A2562, Revision 3, dated July
11, 2013.
(1) Do an external detailed inspection for
cracks in the side panel webs, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2562,
Revision 3, dated July 11, 2013.
(2) Do an internal detailed inspection and
high frequency eddy current (HFEC)
inspection for cracks in the top and side
panel stiffeners, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2562, Revision 3,
dated July 11, 2013.
(3) Do an external detailed inspection for
cracks in the top panel web, in accordance
with the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2562,
Revision 3, dated July 11, 2013.
(k) Exception to Boeing Service Bulletin 747–
53A2562, Revision 3, Dated July 11, 2013
Where paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 747–53A2562,
Revision 3, dated July 11, 2013, specifies a
compliance time relative to the ‘‘Revision 3
date of this service bulletin,’’ this AD
requires compliance within the specified
compliance time after the effective date of
this AD.
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(l) NWW Modification for Certain Airplanes
For airplanes identified in Boeing Alert
Service Bulletin 747–53A2808, dated
November 30, 2012: At the applicable time
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2808,
dated November 30, 2012, replace the left
side, right side, and top panels of the NWW,
as applicable, with new panels, in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2808, dated November 30, 2012.
Concurrently with doing the replacement
specified in this paragraph, do a detailed
inspection for cracks of the attaching
structural elements that are common to the
removed top, left side, and right side panels
of the NWW, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2808, dated
November 30, 2012. If any crack is found,
before further flight, repair the cracking using
a method approved in accordance with the
procedures specified in paragraph (p) of this
AD.
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(m) Repetitive Post-Modification Inspections
for Certain Airplanes
For airplanes on which the replacement
specified in paragraph (l) of this AD has been
done: At the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2808, dated
November 30, 2012, do the actions specified
in paragraphs (m)(1), (m)(2), and (m)(3) of
this AD. If any crack is found: Before further
flight, repair the cracking using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD. Repeat
the inspections specified in paragraphs
(m)(1), (m)(2), and (m)(3) of this AD
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2808, dated
November 30, 2012.
(1) Do an external detailed inspection for
cracks in the side panel webs, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2808,
dated November 30, 2012.
(2) Do an internal detailed inspection and
HFEC inspection for cracks in the top and
side panel stiffeners, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2808, dated
November 30, 2012.
(3) Do an external detailed inspection for
cracks in the top panel web, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2808,
dated November 30, 2012.
(n) Terminating Action for Certain
Repetitive Inspections
Replacing the left side, right side, and top
panels of the NWW with new panels as
specified in paragraph (i) or (l) of this AD
terminates the repetitive inspections required
by paragraph (g) of this AD.
(o) Credit for Previous Actions
(1) This paragraph restates the credit given
in paragraph (k) of AD 2006–22–15.
(i) This paragraph provides credit for the
actions required by paragraph (g)(1) of this
AD, if those actions were performed before
January 27, 2005 (the effective date of AD
2004–25–23, Amendment 39–13911 (69 FR
76839, December 23, 2004)), using Boeing
Alert Service Bulletin 747–53A2465, dated
April 5, 2001, which is not incorporated by
reference in this AD.
(ii) This paragraph provides credit for
actions required by paragraphs (g)(1) and
(g)(2) of this AD, if those actions were
performed before December 11, 2006 (the
effective date of AD 2006–22–15), using a
service bulletin identified in paragraph
(o)(1)(ii)(A), (o)(1)(ii)(B), or (o)(1)(ii)(C) of this
AD, which are not incorporated by reference
in this AD.
(A) Boeing Alert Service Bulletin 747–
53A2465, Revision 1, dated October 16, 2003.
(B) Boeing Alert Service Bulletin 747–
53A2465, Revision 2, dated November 11,
2004.
(C) Boeing Alert Service Bulletin 747–
53A2465, Revision 3, dated December 23,
2004.
(2) This paragraph provides credit for the
actions required by paragraph (g) of this AD,
if those actions were performed before the
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
effective date of this AD using Boeing Alert
Service Bulletin 747–53A2465, Revision 4,
dated February 24, 2005, which is not
incorporated by reference in this AD.
(3) This paragraph provides credit for the
actions required by paragraphs (i) and (j) of
this AD, if those actions were performed
before the effective date of this AD using the
service information identified in paragraph
(o)(3)(i) or (o)(3)(ii) of this AD.
(i) Boeing Service Bulletin 747–53A2562,
Revision 1, dated July 28, 2005, which was
incorporated by reference in AD 2006–22–15.
(ii) Boeing Service Bulletin 747–53A2562,
Revision 2, dated May 31, 2007, which is not
incorporated by reference in this AD.
(p) 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 (q)(1) 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,
modification, or alteration 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. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOC actions approved previously for
AD 2006–22–15 are approved as AMOCs for
the corresponding actions of this AD. The
compliance times in AMOCs approved
previously for AD 2006–22–15 are not
approved for the corresponding actions and
compliance times in this AD, if this AD
specifies an earlier compliance time than that
specified in AD 2006–22–15. Compliance
times in AMOCs approved previously for AD
2006–22–15 that meet the requirements of
this AD are acceptable.
(q) Related Information
(1) For more information about this AD,
contact Bill Ashforth, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6432; fax: 425–
917–6590; email: Bill.Ashforth@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
E:\FR\FM\18MRR1.SGM
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(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 Alert Service Bulletin 747–
53A2808, dated November 30, 2012.
(ii) Boeing Service Bulletin 747–53A2465,
Revision 5, dated July 11, 2013.
(iii) Boeing Service Bulletin 747–53A2562,
Revision 3, dated July 11, 2013.
(3) For Boeing 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 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.
(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.
Issued in Renton, Washington, on March 9,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–06001 Filed 3–17–16; 8:45 am]
BILLING CODE 4910–13–P
actions if necessary. This AD also
provides an optional preventive
modification that terminates the
inspections at the modified location. We
are issuing this AD to detect and correct
fatigue cracking around fastener
locations that could cause multiple
window corner skin cracks, which
could result in rapid decompression and
loss of structural integrity of the
airplane.
This AD is effective April 22,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 22, 2016.
DATES:
For service information
identified in this final rule, 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0495.
ADDRESSES:
Examining the AD Docket
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–0495; Directorate
Identifier 2014–NM–172–AD; Amendment
39–18435; AD 2016–06–04]
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 737–300,
–400, and –500 series airplanes. This
AD was prompted by reports of cracking
at certain fastener locations in the
window corners of the window belt
area. This AD requires repetitive high
frequency eddy current (HFEC)
inspections for fatigue cracking in
certain fastener locations in the window
corners of the window belt area, and
related investigative and corrective
asabaliauskas on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
18:10 Mar 17, 2016
Jkt 238001
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
0495; 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:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
faa.gov.
SUPPLEMENTARY INFORMATION:
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14711
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–300, –400, and –500 series
airplanes. The NPRM published in the
Federal Register on March 24, 2015 (80
FR 15523) (‘‘the NPRM’’). The NPRM
was prompted by reports of cracking at
certain fastener locations in the window
corners of the window belt area. The
NPRM proposed to require repetitive
HFEC inspections for fatigue cracking in
certain fastener locations in the window
corners of the window belt area, and
related investigative and corrective
actions if necessary. We are issuing this
AD to detect and correct fatigue
cracking around fastener locations that
could cause multiple window corner
skin cracks, which could result in rapid
decompression and loss of structural
integrity of the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request for Clarification of Location of
the Twelve Fastener Inspections
Southwest Airlines (SWA) requested
that a correction be made to paragraph
(g) of the proposed AD to clarify the
areas for the inspection of the twelve
fastener locations. SWA noted that
paragraph (g) of the proposed AD stated
to inspect locations ‘‘at the upper
forward and lower aft corners of each
window between station (STA) 360 and
STA 540 and between STA 727 and
STA 908.’’ SWA stated that between
STA 727 and STA 908, Boeing Alert
Service Bulletin 737–53A1328, dated
July 22, 2014, specifies the location as
the lower forward and upper aft corners.
We agree with the commenter for the
reason provided. We have revised
paragraph (g) of this AD to require an
inspection of the twelve fastener
locations at the upper forward and
lower aft corners of each window
between STA 360 and STA 540 and at
the upper aft and lower forward corners
of each window between STA 727 and
STA 908.
Request for Clarification of the Intent of
the Inspection Requirements in
Paragraph (g) of the Proposed AD
SWA requested that we clarify the
intent of paragraph (g) of the proposed
AD. SWA stated that paragraph (g) of
the proposed AD states to accomplish
the inspections at the times specified in
tables 1 and 2 of paragraph 1.E.,
E:\FR\FM\18MRR1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 53 (Friday, March 18, 2016)]
[Rules and Regulations]
[Pages 14707-14711]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06001]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0774; Directorate Identifier 2013-NM-154-AD;
Amendment 39-18438; AD 2016-06-07]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2006-22-15 for
all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B,
747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and
747SP series airplanes. AD 2006-22-15 required repetitive inspections
for cracking of certain panel webs and stiffeners of the nose wheel
well (NWW), and corrective actions if necessary; and replacement of
certain panels with new panels, which terminates the repetitive
inspections. This new AD reduces a compliance time and adds certain
inspections and an applicable repair. This AD was prompted by multiple
reports of fatigue cracking in the NWW top panel and side panel webs
and stiffeners. We are issuing this AD to prevent fatigue cracking of
the NWW side and top panels, which could result in a NWW
depressurization event severe enough to reduce the structural integrity
of the fuselage.
DATES: This AD is effective April 22, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 22,
2016.
ADDRESSES: For service information identified in this final rule,
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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0774.
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-2014-
0774; 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 supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2006-22-15, Amendment 39-14812 (71
FR 64884, November 6, 2006) (``AD 2006-22-15''). AD 2006-22-15 applied
to all The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-
200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR,
and 747SP series airplanes. The SNPRM published in the Federal Register
on September 18, 2015 (80 FR 56407) (``the SNPRM''). We preceded the
SNPRM with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on November 17, 2014 (79 FR 68388) (``the NPRM''). The
NPRM proposed to continue to require repetitive inspections for
cracking of
[[Page 14708]]
certain panel webs and stiffeners of the NWW, and corrective actions if
necessary; and replacement of certain panels with new panels, which
terminates the repetitive inspections. The NPRM proposed to reduce a
compliance time and add certain inspections and repair if necessary.
The NPRM was prompted by reports of fatigue cracking in the panel webs
and stiffeners of the NWW found prior to the inspection threshold of AD
2006-22-15. The SNPRM revised the NPRM by specifying a repetitive
inspection interval for a certain NWW area inspection. We are issuing
this AD to prevent fatigue cracking of the NWW side and top panels,
which could result in a NWW depressurization event severe enough to
reduce the structural integrity of the fuselage.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM and
the FAA's response to each comment.
Support for the SNPRM
Two commenters supported the SNPRM. One commenter stated that the
FAA should continue to execute its administrative power to ensure
traveler safety and industry compliance, adding that while the original
rule was good, ensuring that specifics are covered and timetables are
available is an important improvement.
Request for Credit for Compliance Times in Previously Approved
Alternative Methods of Compliance (AMOCs)
Boeing requested that we allow credit for the compliance times in
previously approved AMOCs, if the compliance times are acceptable
according to the SNPRM.
We agree with the commenter's request. We have revised paragraph
(p)(4) of this AD to state that: AMOC actions approved previously for
AD 2006-22-15 are approved as AMOCs for the corresponding actions of
this AD. In addition, paragraph (p)(4) of this AD states that the
compliance times in AMOCs approved previously for AD 2006-22-15 are not
approved for the corresponding actions and compliance times in this AD,
if this AD specifies an earlier compliance time than that specified in
AD 2006-22-15; and that compliance times in AMOCs approved previously
for AD 2006-22-15 that meet the requirements of this AD are acceptable.
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 change described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following Boeing service bulletins.
Boeing Alert Service Bulletin 747-53A2808, dated November
30, 2012. This service information describes procedures for replacement
of the side and top panel webs, support beams, and stiffeners of the
NWW; an inspection for cracking of the attaching structural elements
that are common to the removed top and side panels of the NWW;
repetitive post-modification inspections for cracks in the top and side
panel webs and stiffeners; and repairs.
Boeing Service Bulletin 747-53A2465, Revision 5, dated
July 11, 2013. This service information describes procedures for doing
inspections for cracking of the NWW side panel and top panel webs and
longitudinal stiffeners for cracks, and related investigative and
corrective actions.
Boeing Service Bulletin 747-53A2562, Revision 3, dated
July 11, 2013. This service information describes procedures for
replacement of the side and top panel webs and certain stiffeners of
the NWW; an inspection for cracks in attaching structural elements that
are common to the removed top panel and side panels; repetitive post-
modification inspections for cracks in the top and side panel webs and
stiffeners; and repairs.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Costs of Compliance
We estimate that this AD will affect 255 airplanes of U.S.
registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections [actions retained 119 work-hours x $0................ $10,115 per $2,579,325 per
from AD 2006-22-15]. $85 per hour = inspection cycle. inspection cycle.
$10,115 per
inspection cycle.
Modification [actions retained Up to 1,346 work- Up to $144,248.... Up to $258,658.... Up to $65,957,790.
from AD 2006-22-15]. hours x $85 per
hour = $114,410.
Post-modification Inspections 119 work-hours x $0................ $10,115 per $2,579,325 per
[new action]. $85 per hour = inspection cycle. inspection cycle.
$10,115 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
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
[[Page 14709]]
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(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 removing Airworthiness Directive (AD)
2006-22-15, Amendment 39-14812 (71 FR 64884, November 6, 2006) (``AD
2006-22-15''), and adding the following new AD:
2016-06-07 The Boeing Company: Amendment 39-18438; Docket No. FAA-
2014-0774; Directorate Identifier 2013-NM-154-AD.
(a) Effective Date
This AD is effective April 22, 2016.
(b) Affected ADs
This AD replaces AD 2006-22-15, Amendment 39-14812 (71 FR 64884,
November 6, 2006) (``AD 2006-22-15'').
(c) Applicability
This AD applies to all The Boeing Company Model 747-100, 747-
100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400,
747-400D, 747-400F, 747SR, and 747SP series airplanes, certificated
in any category.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by multiple reports of cracking in the nose
wheel well (NWW) top panel and side panel webs and stiffeners. We
are issuing this AD to prevent fatigue cracking of the NWW side and
top panels, which could result in a NWW depressurization event
severe enough to reduce the structural integrity of the fuselage.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections and Corrective Actions With New Compliance
Times
Except as specified in paragraphs (h)(1) and (h)(2) of this AD,
at the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013: Do the actions specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD, and do all applicable related investigative and
corrective actions; in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2465, Revision 5,
dated July 11, 2013, except as specified in paragraph (h)(3) of this
AD. Do all applicable related investigative and corrective actions
before further flight. Repeat the inspections specified in
paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013. The repetitive interval for the inspection of Area 2 specified
in table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, is 1,000
flight cycles. In table 2 and table 3 in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2465, Revision 5,
dated July 11, 2013, the date ``January 27, 2005,'' is the effective
date of AD 2004-25-23, Amendment 39-13911 (69 FR 76839, December 23,
2004); and the date ``May 10, 2005,'' is the effective date of AD
2005-09-02, Amendment 39-14070 (70 FR 21141, April 25, 2005;
corrected May 25, 2005 (70 FR 29940)).
(1) Do an external detailed inspection for cracks of the top and
sidewall panel webs of the NWW (specified as Area 1 and Area 2 in
Boeing Service Bulletin 747-53A2465, Revision 5, dated July 11,
2013).
(2) Do internal detailed and surface high frequency eddy current
(HFEC) inspections for cracks of the sidewall panel and top panel
stiffeners of the NWW (specified as Area 3 in Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013).
(3) Do an external detailed and ultrasonic testing (UT)
inspection for cracks of the top and sidewall panel webs of the NWW
(specified as Area 1 and Area 2 in Boeing Service Bulletin 747-
53A2465, Revision 5, dated July 11, 2013).
(h) Exceptions to Boeing Service Bulletin 747-53A2465, Revision 5,
Dated July 11, 2013
(1) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, applies to
airplanes with less than 15,000 total flight cycles ``as of the
Revision 5 date of this service bulletin.'' For this AD, however,
table 1 applies to airplanes with the specified total flight cycles
as of the effective date of this AD.
(2) Table 1 in paragraph 1.E., ``Compliance,'' of Boeing Service
Bulletin 747-53A2465, Revision 5, dated July 11, 2013, specifies a
compliance time of ``13,000 total flight-cycles,'' or ``within 1,000
flight cycles after the Revision 5 date of this service bulletin,''
whichever occurs later. This AD requires compliance before the
accumulation of 10,000 total flight cycles or within 1,000 flight
cycles after the effective date of this AD, whichever occurs later.
(3) If any cracking or damage is found during any inspection
required by paragraph (g) of this AD, and Boeing Service Bulletin
747-53A2465, Revision 5, dated July 11, 2013, specifies to contact
Boeing for appropriate action: Before further flight, repair the
cracking or damage using a method approved in accordance with the
procedures specified in paragraph (p) of this AD.
(i) NWW Modification
For airplanes identified in Boeing Service Bulletin 747-53A2562,
Revision 3, dated July 11, 2013: At the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013, replace the left-side,
right-side, and top panels of the NWW, as applicable, with new
panels, in accordance with the Accomplishment Instructions of Boeing
Service Bulletin 747-53A2562, Revision 3, dated July 11, 2013. As of
the effective date of this AD, concurrently with doing the
replacement specified in Boeing Service Bulletin 747-53A2562,
Revision 3, dated July 11, 2013, do a detailed inspection for any
cracks or damage (including, but not limited to, dents and
corrosion) in all attaching structural elements that are common to
the removed top panel and side panels, as applicable, and do all
applicable corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2562, Revision 3,
dated July 11, 2013. If any crack or damage is found, before further
flight, repair the cracking or damage using a method approved in
accordance with the procedures specified in paragraph (p) of this
AD. In paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2562, Revision 3, dated July 11, 2013, the date ``December
11, 2006,'' is the effective date of AD 2006-22-15.
[[Page 14710]]
(j) Repetitive Post-Modification Inspections
For airplanes on which the replacement specified in paragraph
(i) of this AD has been done: Except as required by paragraph (k) of
this AD, at the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2562, Revision 3,
dated July 11, 2013, do the actions specified in paragraphs (j)(1),
(j)(2), and (j)(3) of this AD. If any crack is found: Before further
flight, repair the cracking using a method approved in accordance
with the procedures specified in paragraph (p) of this AD. Repeat
the inspections specified in paragraphs (j)(1), (j)(2), and (j)(3)
of this AD thereafter at the applicable intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2562, Revision 3, dated July 11, 2013.
(1) Do an external detailed inspection for cracks in the side
panel webs, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.
(2) Do an internal detailed inspection and high frequency eddy
current (HFEC) inspection for cracks in the top and side panel
stiffeners, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.
(3) Do an external detailed inspection for cracks in the top
panel web, in accordance with the Accomplishment Instructions of
Boeing Service Bulletin 747-53A2562, Revision 3, dated July 11,
2013.
(k) Exception to Boeing Service Bulletin 747-53A2562, Revision 3, Dated
July 11, 2013
Where paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2562, Revision 3, dated July 11, 2013, specifies a compliance
time relative to the ``Revision 3 date of this service bulletin,''
this AD requires compliance within the specified compliance time
after the effective date of this AD.
(l) NWW Modification for Certain Airplanes
For airplanes identified in Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012: At the applicable time specified
in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2808, dated November 30, 2012, replace the left side, right
side, and top panels of the NWW, as applicable, with new panels, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2808, dated November 30, 2012. Concurrently
with doing the replacement specified in this paragraph, do a
detailed inspection for cracks of the attaching structural elements
that are common to the removed top, left side, and right side panels
of the NWW, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
If any crack is found, before further flight, repair the cracking
using a method approved in accordance with the procedures specified
in paragraph (p) of this AD.
(m) Repetitive Post-Modification Inspections for Certain Airplanes
For airplanes on which the replacement specified in paragraph
(l) of this AD has been done: At the applicable time specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2808, dated November 30, 2012, do the actions specified in
paragraphs (m)(1), (m)(2), and (m)(3) of this AD. If any crack is
found: Before further flight, repair the cracking using a method
approved in accordance with the procedures specified in paragraph
(p) of this AD. Repeat the inspections specified in paragraphs
(m)(1), (m)(2), and (m)(3) of this AD thereafter at the applicable
intervals specified in paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 747-53A2808, dated November 30, 2012.
(1) Do an external detailed inspection for cracks in the side
panel webs, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
(2) Do an internal detailed inspection and HFEC inspection for
cracks in the top and side panel stiffeners, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2808, dated November 30, 2012.
(3) Do an external detailed inspection for cracks in the top
panel web, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747-53A2808, dated November 30, 2012.
(n) Terminating Action for Certain Repetitive Inspections
Replacing the left side, right side, and top panels of the NWW
with new panels as specified in paragraph (i) or (l) of this AD
terminates the repetitive inspections required by paragraph (g) of
this AD.
(o) Credit for Previous Actions
(1) This paragraph restates the credit given in paragraph (k) of
AD 2006-22-15.
(i) This paragraph provides credit for the actions required by
paragraph (g)(1) of this AD, if those actions were performed before
January 27, 2005 (the effective date of AD 2004-25-23, Amendment 39-
13911 (69 FR 76839, December 23, 2004)), using Boeing Alert Service
Bulletin 747-53A2465, dated April 5, 2001, which is not incorporated
by reference in this AD.
(ii) This paragraph provides credit for actions required by
paragraphs (g)(1) and (g)(2) of this AD, if those actions were
performed before December 11, 2006 (the effective date of AD 2006-
22-15), using a service bulletin identified in paragraph
(o)(1)(ii)(A), (o)(1)(ii)(B), or (o)(1)(ii)(C) of this AD, which are
not incorporated by reference in this AD.
(A) Boeing Alert Service Bulletin 747-53A2465, Revision 1, dated
October 16, 2003.
(B) Boeing Alert Service Bulletin 747-53A2465, Revision 2, dated
November 11, 2004.
(C) Boeing Alert Service Bulletin 747-53A2465, Revision 3, dated
December 23, 2004.
(2) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Alert Service Bulletin 747-
53A2465, Revision 4, dated February 24, 2005, which is not
incorporated by reference in this AD.
(3) This paragraph provides credit for the actions required by
paragraphs (i) and (j) of this AD, if those actions were performed
before the effective date of this AD using the service information
identified in paragraph (o)(3)(i) or (o)(3)(ii) of this AD.
(i) Boeing Service Bulletin 747-53A2562, Revision 1, dated July
28, 2005, which was incorporated by reference in AD 2006-22-15.
(ii) Boeing Service Bulletin 747-53A2562, Revision 2, dated May
31, 2007, which is not incorporated by reference in this AD.
(p) 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 (q)(1) 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, modification, or alteration 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. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOC actions approved previously for AD 2006-22-15 are
approved as AMOCs for the corresponding actions of this AD. The
compliance times in AMOCs approved previously for AD 2006-22-15 are
not approved for the corresponding actions and compliance times in
this AD, if this AD specifies an earlier compliance time than that
specified in AD 2006-22-15. Compliance times in AMOCs approved
previously for AD 2006-22-15 that meet the requirements of this AD
are acceptable.
(q) Related Information
(1) For more information about this AD, contact Bill Ashforth,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6432;
fax: 425-917-6590; email: Bill.Ashforth@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (r)(3) and (r)(4) of this AD.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference
[[Page 14711]]
(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 Alert Service Bulletin 747-53A2808, dated November
30, 2012.
(ii) Boeing Service Bulletin 747-53A2465, Revision 5, dated July
11, 2013.
(iii) Boeing Service Bulletin 747-53A2562, Revision 3, dated
July 11, 2013.
(3) For Boeing 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 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.
(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 March 9, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-06001 Filed 3-17-16; 8:45 am]
BILLING CODE 4910-13-P
