Airworthiness Directives; the Boeing Company Airplanes, 23893-23897 [2014-07339]
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Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations
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List of Subjects in 7 CFR Part 201
Swine, Hogs, Incorporation by
reference, Livestock, Measurement
standards.
For reasons set forth in the preamble,
9 CFR part 201 is amended as follows:
Register in accordance with 5 U.S.C.
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Information on this material may be
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issuing this AD to detect and correct
fatigue cracking of the BS 2598
bulkhead structure, which could
adversely affect the structural integrity
of the bulkhead and the horizontal
stabilizer support structure, and result
in loss of controllability of the airplane.
DATES: This AD is effective June 3, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 3, 2014
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.
Larry Mitchell,
Administrator, Grain Inspection, Packers and
Stockyards Administration.
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–
0425; 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:
Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6428; fax:
425–917–6590; email:
nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
[FR Doc. 2014–09655 Filed 4–28–14; 8:45 am]
BILLING CODE 3410–KD–P
PART 201—REGULATIONS UNDER
THE PACKERS AND STOCKYARDS
ACT
DEPARTMENT OF TRANSPORTATION
1. The authority citation for part 201
continues to read as follows:
■
Federal Aviation Administration
Authority: 7 U.S.C. 181–229c.
14 CFR Part 39
2. In § 201.71, paragraph (a) is revised
to read as follows:
[Docket No. FAA–2013–0425; Directorate
Identifier 2012–NM–224–AD; Amendment
39–17815; AD 2014–07–01]
§ 201.71 Scales; accurate weights, repairs,
adjustments or replacements after
inspection.
RIN 2120–AA64
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■
(a) All scales used by stockyard
owners, swine contractors, market
agencies, dealers, packers, and live
poultry dealers to weigh livestock,
livestock carcasses, live poultry, or feed
for the purpose of purchase, sale
acquisition, payment, or settlement
shall be installed, maintained, and
operated to ensure accurate weights.
Such scales shall meet applicable
requirements contained in section 5.59,
Electronic Livestock, Meat, and Poultry
Evaluation Systems and/or Devices,
pages 5–85 and 5–86 of the ‘‘U.S.
Department of Commerce, National
Institute of Standards and Technology,
Specifications, Tolerances, and other
Technical Requirements for Weighing
and Measuring Devices (NIST Handbook
44), 2013 edition’’ which is hereby
incorporated by reference. This
incorporation by reference was
approved by the Director of the Federal
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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
airplanes. This AD was prompted by
reports of cracking in particular areas of
the bulkhead structure at body station
(BS) 2598. This AD requires repetitive
inspections, including post-repair and
post-modification inspections, for
cracking in the bulkhead structure at BS
2598; certain one-time inspections of
certain fasteners and support frame
modifications on certain airplanes;
related investigative and corrective
actions, if necessary; and an interim
modification that would terminate
certain repetitive inspections. We are
SUMMARY:
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Discussion
We issued a supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD
that would apply to certain The Boeing
Company Model 747 airplanes. The
SNPRM published in the Federal
Register on January 2, 2014 (79 FR 65).
We preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
May 28, 2013 (78 FR 31867).
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The NPRM proposed to require
repetitive inspections for cracking in the
bulkhead splice fitting, frame supports,
forward and aft inner chords, and floor
support; an inspection for cracking in
the bulkhead upper web, doubler, and
bulkhead lower web, and corrective
actions if necessary; and repetitive postrepair inspections of the support frame,
and corrective actions, if necessary. For
certain airplanes, the NPRM proposed to
require:
• Inspections for cracking in the
repaired area of the bulkhead, and
corrective actions if necessary;
• A support frame modification and
inspections, and related investigative
and corrective actions, if necessary;
• Repetitive post-repair inspections of
the support frame and inspections for
cracking in the hinge support, and
related investigative and corrective
actions if necessary;
• A one-time inspection of the frame
web and upper shear deck (floor
support) chord aft side for fasteners; and
a one-time inspection of the upper
forward inner chord, frame support
fitting, and splice fitting for the
installation of certain fasteners; and
related investigative and corrective
actions if necessary;
• A one-time inspection of the upper
forward inner chord, frame support
fitting, and splice fitting for the
installation of certain fasteners; a onetime inspection for any repair installed
on the left and right side of the aft inner
chord; and related investigative and
corrective actions, if necessary; and
• A one-time inspection of the
support frame outer chord for cracking,
and repair if necessary.
The NPRM was prompted by reports
of cracking in the forward and aft inner
chord of the BS 2598 bulkhead near the
upper corners of the cutout for the
horizontal stabilizer rear spar, and
cracking in the bulkhead upper and
lower web panels near the inner chord
to shear deck connection.
The SNPRM proposed to add an
optional terminating action for certain
inspections and expand the inspection
area for certain surface and open-hole
high frequency eddy current (HFEC)
inspections. We are issuing this AD to
detect and correct fatigue cracking of the
BS 2598 bulkhead structure, which
could adversely affect the structural
integrity of the bulkhead and the
horizontal stabilizer support structure,
and result in loss of controllability of
the airplane.
Comments
We gave the public the opportunity to
participate in developing this AD. We
have considered the comment received.
Boeing supported the SNPRM (79 FR 65,
January 2, 2014).
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (79 FR 65,
January 2, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (79 FR 65,
January 2, 2014).
Costs of Compliance
We estimate that this AD affects 184
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Parts
cost
Cost per product
Cost on
U.S. operators
0
0
$4,165 per inspection cycle.
26,775 ......................
1,360 ........................
$766,360 per inspection cycle.
Up to $4,926,600.
Up to $250,240.
0
17,000 ......................
3,128,000.
Action
Labor cost
Bulkhead (support frame) inspection ..........
49 work-hours × $85 per hour = $4,165
per inspection cycle.
315 work-hours × $85 per hour = $26,775
16 work-hours × $85 per hour = $1,360 ...
$0
200 work hours × $85 per hour = $17,000
Support frame modification .........................
Support frame upper corner fastener inspection.
Support frame post-modification/post repair
inspection.
We estimate the following costs to do
any necessary interim modification that
would be required based on the results
of inspection of the bulkhead specified
in paragraph (g) of this AD. We have no
way of determining the number of
aircraft that might need this interim
modification:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Interim modification ......................................................
4 work-hours × $85 per hour = $340 ...........................
$0
$340
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We have received no definitive data
that would enable us to provide a cost
estimate for the corrective 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:
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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
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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
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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 adding
the following new airworthiness
directive (AD):
■
2014–07–01 The Boeing Company:
Amendment 39–17815; Docket No.
FAA–2013–0425; Directorate Identifier
2012–NM–224–AD.
(a) Effective Date
This AD is effective June 3, 2014.
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(b) Affected ADs
This AD affects AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010).
(c) Applicability
This AD applies to 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, as identified in Boeing Alert
Service Bulletin 747–53A2427, Revision 7,
dated July 19, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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(e) Unsafe Condition
This AD was prompted by reports of
cracking in particular areas of the bulkhead
structure at body station (BS) 2598. We are
issuing this AD to detect and correct fatigue
cracking of the BS 2598 bulkhead structure,
which could adversely affect the structural
integrity of the bulkhead and the horizontal
stabilizer support structure, and result in loss
of controllability of the airplane.
only. The repetitive inspections of the
bulkhead lower web, as specified in
paragraph (g) of this AD, must be done. If the
aft inner chord repair or upper web repair
specified in Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, has been accomplished, an interim
modification on the side of the airplane that
has the repair is not required by this
paragraph.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(i) Post-Repair Inspection or Post-Interim
Modification Inspection
For airplanes on which an interim
modification, aft inner chord repair, or upper
web repair has been done, as specified in
paragraph (g) or (h) of this AD: At the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2427, Revision 7, dated July
19, 2013, except as specified in paragraph
(m)(1), (m)(2), or (m)(3) of this AD, as
applicable, do the actions specified in
paragraphs (i)(1) and (i)(2) of this AD, and all
applicable corrective actions, in accordance
with the Accomplishment Instructions of
Boeing Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013, except as
required by paragraph (m)(4) of this AD. Do
all applicable corrective actions before
further flight. Repeat the inspections
thereafter at the applicable intervals specified
in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013. Doing the
modification required by paragraph (j) of this
AD terminates the repetitive inspections
required by this paragraph.
(1) Do forward side surface HFEC
inspections for cracking of the bulkhead
forward inner chord, splice fitting, and frame
support.
(2) Do surface and open-hole HFEC
inspections for cracking in the repaired and
modified areas of the bulkhead, as
applicable.
(g) Inspections of the Bulkhead (Support
Frame)
For airplanes on which the bulkhead
(support frame) modification specified in
Boeing Service Bulletin 747–53A2473 or
Boeing Alert Service Bulletin 747–53A2837
has not been done, and on which an interim
modification or aft inner chord repair
specified in Boeing Alert Service Bulletin
747–53A2427 has not been done: At the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2427, Revision 7, dated July
19, 2013, except as provided by paragraph
(m)(1), (m)(2), or (m)(3) of this AD, as
applicable, do an open-hole and surface high
frequency eddy current (HFEC) inspection for
cracking in the bulkhead (support frame),
which includes the bulkhead splice fitting,
frame supports, forward and aft inner chords,
floor supports, and upper and lower web
panels; do a surface HFEC inspection for
cracking in the bulkhead upper web
assembly; do an open-hole and surface HFEC
inspection for cracking in the bulkhead lower
web assembly; and do all applicable
corrective actions; in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2427, Revision 7,
dated July 19, 2013, except as required by
paragraphs (h), (m)(4), (m)(5), and (m)(6) of
this AD. Do all applicable corrective actions
before further flight. Repeat the applicable
inspections, thereafter, at the applicable
times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 747–53A2427, Revision 7, dated July
19, 2013. Doing the modification required by
paragraph (j) of this AD terminates the
repetitive inspections required by this
paragraph.
(h) Interim Modification
For airplanes in Groups 1 and 2, as
identified in Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, on which no cracking was found
during any inspection required by paragraph
(g) of this AD: At the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013, except as
provided by paragraph (m)(2) of this AD, do
the interim modification, in accordance with
the Accomplishment Instructions of Boeing
Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013. Doing the
interim modification terminates the
repetitive inspections required by paragraph
(g) of this AD in the area of the modification
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(j) Bulkhead (Support Frame) Modification
and Inspections
For airplanes on which the bulkhead
(support frame) modification, as specified in
Boeing Service Bulletin 747–53A2473 has
not been done as of the effective date of this
AD: At the applicable time specified in tables
2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011, do the
bulkhead (support frame) modification and
inspections and all applicable related
investigative and corrective actions; in
accordance with steps 3.B.3., 3.B.4., and
3.B.5. of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011, except
as required by paragraph (m)(4) of this AD.
Do all applicable related investigative and
corrective actions before further flight. Doing
the modification in this paragraph terminates
the inspections required by paragraphs (g)
and (i) of this AD.
(k) Post-Modification Inspections
(1) For airplanes on which the bulkhead
(support frame) modification, as specified in
Boeing Service Bulletin 747–53A2473 has
been done: Except as provided by paragraphs
(m)(7) and (m)(8) of this AD, at the applicable
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time specified in tables 6, 7, 8, and 9 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011, do support frame
post-modification inspections, and open-hole
HFEC inspections for cracking in the hinge
support, and do all applicable related
investigative and corrective actions, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011, except as required by paragraph (m)(4)
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Repeat the inspections
thereafter at the applicable times specified in
tables 6, 7, 8, and 9 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2473, Revision 4, dated December 1,
2011.
(2) For airplanes on which the support
frame modification, as specified in Boeing
Service Bulletin 747–53A2473, Revision 1,
dated February 20, 2007 (which is not
incorporated by reference in this AD), has
been done: Except as specified in paragraphs
(m)(7) and (m)(8) of this AD, at the applicable
time specified in tables 4 and 5 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 747–53A2473, Revision 4, dated
December 1, 2011, do a one-time general
visual inspection of the frame web and upper
shear deck (floor support) chord aft side for
fasteners that were installed as part of an
inner chord repair removal; and a one-time
general visual inspection of the upper
forward inner chord, frame support fitting,
and splice fitting for the installation of
certain fasteners; and do all applicable
related investigative and corrective actions;
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011, except as required by paragraph (m)(4)
of this AD. Do all applicable related
investigative and corrective actions at the
applicable times specified in tables 4 and 5
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011.
(3) For airplanes on which the support
frame modification, as specified in Boeing
Service Bulletin 747–53A2473, dated March
24, 2005 (which was incorporated by
reference in AD 2006–05–06, Amendment
39–14503 (71 FR 12125, March 9, 2006)), has
been done: Except as specified in paragraphs
(m)(7) and (m)(8) of this AD, at the applicable
time specified in tables 5 and 10 of paragraph
1.E., ‘‘Compliance,’’ of Boeing Service
Bulletin 747–53A2473, Revision 4, dated
December 1, 2011, do a one-time general
visual inspection of the upper forward inner
chord, frame support fitting, and splice
fitting for the installation of certain fasteners;
a one-time general visual inspection for any
repair installed on the left and right side of
the aft inner chord; and do all applicable
related investigative and corrective actions;
in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011, except as required by paragraph (m)(4)
of this AD. Do all applicable related
investigative and corrective actions at the
applicable times specified in tables 5 and 10
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of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011.
(4) For airplanes on which a postmodification inspection was done using
paragraph 3.B.8. of Part 1 of the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2473, Revision 3,
dated July 14, 2011 (which is not
incorporated by reference in this AD): Except
as required by paragraphs (m)(7) and (m)(8)
of this AD, at the applicable time in table 11
of paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011, do a one-time
surface HFEC inspection of the support frame
outer chord for cracking, in accordance with
Part 1 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011. If any
cracking is found, repair before further flight,
using a method approved in accordance with
the procedures specified in paragraph (q) of
this AD.
(l) Post-Modification and Post-Repair
Inspections
For airplanes on which cracking was found
during a post-modification inspection and
was repaired by doing the installation of an
upper or lower corner post-modification web
crack repair, as specified in Boeing Service
Bulletin 747–53A2473, Revision 4, dated
December 1, 2011: At the applicable times
specified in tables 6 and 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2473, Revision 4, dated December 1,
2011, do a bulkhead (support frame) postrepair inspection, and do all applicable
corrective actions, in accordance with
paragraph a., b., or c. of Part 4 of paragraph
3.B.8 of the Accomplishment Instructions of
Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011, as
applicable, except as required by paragraph
(m)(4) of this AD. Repeat the inspection,
thereafter, at the applicable times specified in
tables 6 and 8 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Service Bulletin
747–53A2473, Revision 4, dated December 1,
2011.
(m) Exceptions to Service Information
(1) Where Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, specifies a compliance time after ‘‘the
date on Revision 2 of this service bulletin,’’
this AD requires compliance within the
specified compliance time after August 28,
2001 (the effective date of AD 2001–15–03,
Amendment 39–12337 (66 FR 38365, July 24,
2001)).
(2) Where Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, specifies a compliance time after ‘‘the
date on Revision 4 of this service bulletin,’’
this AD requires compliance within the
specified compliance time after August 5,
2010 (the effective date of AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010)).
(3) Where Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, specifies a compliance time ‘‘after the
date on the respective service bulletin
revision’’ this AD requires compliance within
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the specified compliance time after the
effective date of this AD.
(4) If any cracking is found during any
inspection required by this AD, and Boeing
Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013; or Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011; specifies to contact
Boeing for appropriate action: Before further
flight, repair the crack using a method
approved in accordance with the procedures
specified in paragraph (q) of this AD.
(5) If, during any inspection required by
paragraph (g) of this AD, any cracking is
found in the bonded web doubler, before
further flight, repair using a method
approved in accordance with the procedures
specified in paragraph (q) of this AD.
(6) Where Part 1 of the Accomplishment
Instructions of Boeing Alert Service Bulletin
747–53A2427, Revision 7, dated July 19,
2013, specifies accomplishing inspections for
cracking in the forward and aft inner chords,
splice fittings, floor supports, and upper and
lower web panels, this AD also requires
doing an open-hole HFEC inspection of the
bonded web doubler if present.
(7) Where Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011, specifies a compliance time ‘‘after the
date on Revision 2 of this service bulletin,’’
this AD requires compliance within the
specified compliance time as of August 5,
2010 (the effective date of AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010)).
(8) Where Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011, specifies a compliance time ‘‘after the
date on Revision 3 of this service bulletin,’’
or ‘‘after the date on Revision 4 of this service
bulletin,’’ this AD requires compliance
within the specified compliance time ‘‘after
the effective date of this AD.’’
(n) Optional Terminating Modification
Accomplishing the modification of the
bulkhead at BS 2598 in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2837, dated July 13,
2012, terminates the requirements of
paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, except where Boeing Alert Service
Bulletin 747–53A2837, dated July 13, 2012,
specifies to contact Boeing for appropriate
action: Before further flight, repair the crack
using a method approved in accordance with
the procedures specified in paragraph (q) of
this AD.
(o) Terminating Action for Certain
Requirements of AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010)
(1) Accomplishing the inspections, repairs,
and modification in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011, is an acceptable
terminating action for the corresponding
inspections, repairs, and modification at the
BS 2598 support frame required by
paragraphs (i), (j), (k), (1), (m), (n), (o), (p), (q),
(r), (s), (t), (u), and (v) of AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010). Where Boeing Service Bulletin 747–
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29APR1
Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations
53A2473, Revision 4, dated December 1,
2011, specifies to contact Boeing for repair
instructions, the repair instructions must be
approved in accordance with the procedures
specified in paragraph (q) of this AD. All
provisions of AD 2010–14–07 that are not
specifically referenced in this paragraph
remain fully applicable and must be
complied with.
(2) Accomplishing the inspections, repairs,
and interim modification in accordance with
Boeing Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013, is an
acceptable terminating action for the
corresponding inspections, repairs and
interim modification at the BS 2598 bulkhead
required by paragraphs (i), (j), (o), (s), (t), (u),
and (v) of AD 2010–14–07, Amendment 39–
16352 (75 FR 38001, July 1, 2010). Where
Boeing Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013, specifies to
contact Boeing for repair data, the repair data
must be approved in accordance with the
procedures specified in paragraph (q) of this
AD. All provisions of AD 2010–14–07 that
are not specifically referenced in this
paragraph remain fully applicable and must
be complied with.
sroberts on DSK5SPTVN1PROD with RULES
(p) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraphs (g), (h), (i),
and (n)(2) of this AD, if those actions were
performed before the effective date of this AD
using Boeing Alert Service Bulletin 747–
53A2427, Revision 6, dated July 14, 2011,
provided that the additional actions added in
Boeing Alert Service Bulletin 747–53A2427,
Revision 7, dated July 19, 2013, are done
within the applicable compliance times
specified in paragraphs (g), (h), and (i) of this
AD. Boeing Alert Service Bulletin 747–
53A2427, Revision 6, dated July 14, 2011, is
not incorporated by reference in this AD.
(q) 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 (r)(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
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Related portions or applicable
paragraphs of AMOCs approved previously
VerDate Mar<15>2010
15:55 Apr 28, 2014
Jkt 232001
in accordance with AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010), are approved as AMOCs for the
corresponding provisions of paragraphs (g),
(h), (i), (j), (k), and (l) of this AD. All new
actions specified in paragraphs (g), (h), (i), (j),
(k), and (l) of this AD that are not identified
in a previously approved AMOC must still be
done.
(1) For more information about this AD,
contact Nathan Weigand, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle ACO, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; phone: 425–917–
6428; fax: 425–917–6590; email:
nathan.p.weigand@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference in
this AD may be viewed at the addresses
specified in paragraphs (s)(3) and (s)(4) of
this AD.
(s) 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 Alert Service Bulletin 747–
53A2427, Revision 7, dated July 19, 2013.
(ii) Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011.
(iii) Boeing Alert Service Bulletin 747–
53A2837, dated July 13, 2012.
(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/ibrlocations.html.
Issued in Renton, Washington, on March
17, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–07339 Filed 4–28–14; 8:45 am]
BILLING CODE 4910–13–P
Frm 00011
Fmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0020; Directorate
Identifier 2013–CE–039–AD; Amendment
39–17821; AD 2014–07–07]
RIN 2120–AA64
(r) Related Information
PO 00000
23897
Sfmt 4700
Airworthiness Directives; British
Aerospace (Operations) Limited
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding an
airworthiness directive (AD) 87–02–04
for British Aerospace (Operations)
Limited Model HP.137 Jetstream MK.1,
Jetstream Series 200, and Jetstream
Series 3101 airplanes. This AD results
from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as cracking of the forward
main landing gear yoke pintle resulting
from corrosion pits leading to stress
corrosion. We are issuing this AD to
require actions to address the unsafe
condition on these products.
DATES: This AD is effective June 3, 2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of June 3, 2014.
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0020; or in person at the 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 service information identified in
this AD, contact BAE Systems
(Operations) Ltd, Customer Information
Department, Prestwick International
Airport, Ayrshire, KA9 2RW, Scotland,
United Kingdom; phone: +44 1292
675207, fax: +44 1292 675704; email:
RApublications@baesystems.com;
Internet: https://
www.jetstreamcentral.com. You may
view this referenced service information
at the FAA, Small Airplane Directorate,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148.
SUMMARY:
E:\FR\FM\29APR1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 82 (Tuesday, April 29, 2014)]
[Rules and Regulations]
[Pages 23893-23897]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-07339]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0425; Directorate Identifier 2012-NM-224-AD;
Amendment 39-17815; AD 2014-07-01]
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 airplanes. This AD was prompted by reports
of cracking in particular areas of the bulkhead structure at body
station (BS) 2598. This AD requires repetitive inspections, including
post-repair and post-modification inspections, for cracking in the
bulkhead structure at BS 2598; certain one-time inspections of certain
fasteners and support frame modifications on certain airplanes; related
investigative and corrective actions, if necessary; and an interim
modification that would terminate certain repetitive inspections. We
are issuing this AD to detect and correct fatigue cracking of the BS
2598 bulkhead structure, which could adversely affect the structural
integrity of the bulkhead and the horizontal stabilizer support
structure, and result in loss of controllability of the airplane.
DATES: This AD is effective June 3, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 3, 2014
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-
0425; 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: Nathan Weigand, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428; fax:
425-917-6590; email: nathan.p.weigand@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 by adding an AD that would apply to certain The
Boeing Company Model 747 airplanes. The SNPRM published in the Federal
Register on January 2, 2014 (79 FR 65). We preceded the SNPRM with a
notice of proposed rulemaking (NPRM) that published in the Federal
Register on May 28, 2013 (78 FR 31867).
[[Page 23894]]
The NPRM proposed to require repetitive inspections for cracking in
the bulkhead splice fitting, frame supports, forward and aft inner
chords, and floor support; an inspection for cracking in the bulkhead
upper web, doubler, and bulkhead lower web, and corrective actions if
necessary; and repetitive post-repair inspections of the support frame,
and corrective actions, if necessary. For certain airplanes, the NPRM
proposed to require:
Inspections for cracking in the repaired area of the
bulkhead, and corrective actions if necessary;
A support frame modification and inspections, and related
investigative and corrective actions, if necessary;
Repetitive post-repair inspections of the support frame
and inspections for cracking in the hinge support, and related
investigative and corrective actions if necessary;
A one-time inspection of the frame web and upper shear
deck (floor support) chord aft side for fasteners; and a one-time
inspection of the upper forward inner chord, frame support fitting, and
splice fitting for the installation of certain fasteners; and related
investigative and corrective actions if necessary;
A one-time inspection of the upper forward inner chord,
frame support fitting, and splice fitting for the installation of
certain fasteners; a one-time inspection for any repair installed on
the left and right side of the aft inner chord; and related
investigative and corrective actions, if necessary; and
A one-time inspection of the support frame outer chord for
cracking, and repair if necessary.
The NPRM was prompted by reports of cracking in the forward and aft
inner chord of the BS 2598 bulkhead near the upper corners of the
cutout for the horizontal stabilizer rear spar, and cracking in the
bulkhead upper and lower web panels near the inner chord to shear deck
connection.
The SNPRM proposed to add an optional terminating action for
certain inspections and expand the inspection area for certain surface
and open-hole high frequency eddy current (HFEC) inspections. We are
issuing this AD to detect and correct fatigue cracking of the BS 2598
bulkhead structure, which could adversely affect the structural
integrity of the bulkhead and the horizontal stabilizer support
structure, and result in loss of controllability of the airplane.
Comments
We gave the public the opportunity to participate in developing
this AD. We have considered the comment received. Boeing supported the
SNPRM (79 FR 65, January 2, 2014).
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting
this AD as proposed except for minor editorial changes. We have
determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (79 FR 65, January 2, 2014) for correcting the unsafe condition;
and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (79 FR 65, January 2, 2014).
Costs of Compliance
We estimate that this AD affects 184 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Bulkhead (support frame) 49 work-hours x $85 per $0 $4,165 per $766,360 per
inspection. hour = $4,165 per inspection cycle. inspection cycle.
inspection cycle.
Support frame modification....... 315 work-hours x $85 per 0 26,775.............. Up to $4,926,600.
hour = $26,775.
Support frame upper corner 16 work-hours x $85 per 0 1,360............... Up to $250,240.
fastener inspection. hour = $1,360.
Support frame post-modification/ 200 work hours x $85 per 0 17,000.............. 3,128,000.
post repair inspection. hour = $17,000.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary interim
modification that would be required based on the results of inspection
of the bulkhead specified in paragraph (g) of this AD. We have no way
of determining the number of aircraft that might need this interim
modification:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Interim modification...................... 4 work-hours x $85 per hour = $340 $0 $340
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
a cost estimate for the corrective 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
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
[[Page 23895]]
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):
2014-07-01 The Boeing Company: Amendment 39-17815; Docket No. FAA-
2013-0425; Directorate Identifier 2012-NM-224-AD.
(a) Effective Date
This AD is effective June 3, 2014.
(b) Affected ADs
This AD affects AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010).
(c) Applicability
This AD applies to 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, as identified in Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking in particular areas
of the bulkhead structure at body station (BS) 2598. We are issuing
this AD to detect and correct fatigue cracking of the BS 2598
bulkhead structure, which could adversely affect the structural
integrity of the bulkhead and the horizontal stabilizer support
structure, and result in loss of controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections of the Bulkhead (Support Frame)
For airplanes on which the bulkhead (support frame) modification
specified in Boeing Service Bulletin 747-53A2473 or Boeing Alert
Service Bulletin 747-53A2837 has not been done, and on which an
interim modification or aft inner chord repair specified in Boeing
Alert Service Bulletin 747-53A2427 has not been done: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013, except as provided by paragraph (m)(1), (m)(2), or (m)(3)
of this AD, as applicable, do an open-hole and surface high
frequency eddy current (HFEC) inspection for cracking in the
bulkhead (support frame), which includes the bulkhead splice
fitting, frame supports, forward and aft inner chords, floor
supports, and upper and lower web panels; do a surface HFEC
inspection for cracking in the bulkhead upper web assembly; do an
open-hole and surface HFEC inspection for cracking in the bulkhead
lower web assembly; and do all applicable corrective actions; in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013,
except as required by paragraphs (h), (m)(4), (m)(5), and (m)(6) of
this AD. Do all applicable corrective actions before further flight.
Repeat the applicable inspections, thereafter, at the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013. Doing
the modification required by paragraph (j) of this AD terminates the
repetitive inspections required by this paragraph.
(h) Interim Modification
For airplanes in Groups 1 and 2, as identified in Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, on
which no cracking was found during any inspection required by
paragraph (g) of this AD: At the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as provided by
paragraph (m)(2) of this AD, do the interim modification, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013. Doing
the interim modification terminates the repetitive inspections
required by paragraph (g) of this AD in the area of the modification
only. The repetitive inspections of the bulkhead lower web, as
specified in paragraph (g) of this AD, must be done. If the aft
inner chord repair or upper web repair specified in Boeing Alert
Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013, has
been accomplished, an interim modification on the side of the
airplane that has the repair is not required by this paragraph.
(i) Post-Repair Inspection or Post-Interim Modification Inspection
For airplanes on which an interim modification, aft inner chord
repair, or upper web repair has been done, as specified in paragraph
(g) or (h) of this AD: At the applicable times specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
747-53A2427, Revision 7, dated July 19, 2013, except as specified in
paragraph (m)(1), (m)(2), or (m)(3) of this AD, as applicable, do
the actions specified in paragraphs (i)(1) and (i)(2) of this AD,
and all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, except as required by
paragraph (m)(4) of this AD. Do all applicable corrective actions
before further flight. Repeat the inspections thereafter at the
applicable intervals specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 747-53A2427, Revision 7, dated July
19, 2013. Doing the modification required by paragraph (j) of this
AD terminates the repetitive inspections required by this paragraph.
(1) Do forward side surface HFEC inspections for cracking of the
bulkhead forward inner chord, splice fitting, and frame support.
(2) Do surface and open-hole HFEC inspections for cracking in
the repaired and modified areas of the bulkhead, as applicable.
(j) Bulkhead (Support Frame) Modification and Inspections
For airplanes on which the bulkhead (support frame)
modification, as specified in Boeing Service Bulletin 747-53A2473
has not been done as of the effective date of this AD: At the
applicable time specified in tables 2 and 3 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do the bulkhead (support frame) modification
and inspections and all applicable related investigative and
corrective actions; in accordance with steps 3.B.3., 3.B.4., and
3.B.5. of the Accomplishment Instructions of Boeing Service Bulletin
747-53A2473, Revision 4, dated December 1, 2011, except as required
by paragraph (m)(4) of this AD. Do all applicable related
investigative and corrective actions before further flight. Doing
the modification in this paragraph terminates the inspections
required by paragraphs (g) and (i) of this AD.
(k) Post-Modification Inspections
(1) For airplanes on which the bulkhead (support frame)
modification, as specified in Boeing Service Bulletin 747-53A2473
has been done: Except as provided by paragraphs (m)(7) and (m)(8) of
this AD, at the applicable
[[Page 23896]]
time specified in tables 6, 7, 8, and 9 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do support frame post-modification
inspections, and open-hole HFEC inspections for cracking in the
hinge support, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, except as required by paragraph (m)(4) of
this AD. Do all applicable related investigative and corrective
actions before further flight. Repeat the inspections thereafter at
the applicable times specified in tables 6, 7, 8, and 9 of paragraph
1.E., ``Compliance,'' of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011.
(2) For airplanes on which the support frame modification, as
specified in Boeing Service Bulletin 747-53A2473, Revision 1, dated
February 20, 2007 (which is not incorporated by reference in this
AD), has been done: Except as specified in paragraphs (m)(7) and
(m)(8) of this AD, at the applicable time specified in tables 4 and
5 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do a one-time general
visual inspection of the frame web and upper shear deck (floor
support) chord aft side for fasteners that were installed as part of
an inner chord repair removal; and a one-time general visual
inspection of the upper forward inner chord, frame support fitting,
and splice fitting for the installation of certain fasteners; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, except as
required by paragraph (m)(4) of this AD. Do all applicable related
investigative and corrective actions at the applicable times
specified in tables 4 and 5 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
(3) For airplanes on which the support frame modification, as
specified in Boeing Service Bulletin 747-53A2473, dated March 24,
2005 (which was incorporated by reference in AD 2006-05-06,
Amendment 39-14503 (71 FR 12125, March 9, 2006)), has been done:
Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at
the applicable time specified in tables 5 and 10 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do a one-time general visual inspection of
the upper forward inner chord, frame support fitting, and splice
fitting for the installation of certain fasteners; a one-time
general visual inspection for any repair installed on the left and
right side of the aft inner chord; and do all applicable related
investigative and corrective actions; in accordance with the
Accomplishment Instructions of Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011, except as required by paragraph
(m)(4) of this AD. Do all applicable related investigative and
corrective actions at the applicable times specified in tables 5 and
10 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin
747-53A2473, Revision 4, dated December 1, 2011.
(4) For airplanes on which a post-modification inspection was
done using paragraph 3.B.8. of Part 1 of the Accomplishment
Instructions of Boeing Service Bulletin 747-53A2473, Revision 3,
dated July 14, 2011 (which is not incorporated by reference in this
AD): Except as required by paragraphs (m)(7) and (m)(8) of this AD,
at the applicable time in table 11 of paragraph 1.E.,
``Compliance,'' of Boeing Service Bulletin 747-53A2473, Revision 4,
dated December 1, 2011, do a one-time surface HFEC inspection of the
support frame outer chord for cracking, in accordance with Part 1 of
the Accomplishment Instructions of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011. If any cracking is
found, repair before further flight, using a method approved in
accordance with the procedures specified in paragraph (q) of this
AD.
(l) Post-Modification and Post-Repair Inspections
For airplanes on which cracking was found during a post-
modification inspection and was repaired by doing the installation
of an upper or lower corner post-modification web crack repair, as
specified in Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011: At the applicable times specified in tables 6 and
8 of paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 747-
53A2473, Revision 4, dated December 1, 2011, do a bulkhead (support
frame) post-repair inspection, and do all applicable corrective
actions, in accordance with paragraph a., b., or c. of Part 4 of
paragraph 3.B.8 of the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, as
applicable, except as required by paragraph (m)(4) of this AD.
Repeat the inspection, thereafter, at the applicable times specified
in tables 6 and 8 of paragraph 1.E., ``Compliance,'' of Boeing
Service Bulletin 747-53A2473, Revision 4, dated December 1, 2011.
(m) Exceptions to Service Information
(1) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after ``the date on
Revision 2 of this service bulletin,'' this AD requires compliance
within the specified compliance time after August 28, 2001 (the
effective date of AD 2001-15-03, Amendment 39-12337 (66 FR 38365,
July 24, 2001)).
(2) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time after ``the date on
Revision 4 of this service bulletin,'' this AD requires compliance
within the specified compliance time after August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
(3) Where Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013, specifies a compliance time ``after the date on
the respective service bulletin revision'' this AD requires
compliance within the specified compliance time after the effective
date of this AD.
(4) If any cracking is found during any inspection required by
this AD, and Boeing Alert Service Bulletin 747-53A2427, Revision 7,
dated July 19, 2013; or Boeing Service Bulletin 747-53A2473,
Revision 4, dated December 1, 2011; specifies to contact Boeing for
appropriate action: Before further flight, repair the crack using a
method approved in accordance with the procedures specified in
paragraph (q) of this AD.
(5) If, during any inspection required by paragraph (g) of this
AD, any cracking is found in the bonded web doubler, before further
flight, repair using a method approved in accordance with the
procedures specified in paragraph (q) of this AD.
(6) Where Part 1 of the Accomplishment Instructions of Boeing
Alert Service Bulletin 747-53A2427, Revision 7, dated July 19, 2013,
specifies accomplishing inspections for cracking in the forward and
aft inner chords, splice fittings, floor supports, and upper and
lower web panels, this AD also requires doing an open-hole HFEC
inspection of the bonded web doubler if present.
(7) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time ``after the date on
Revision 2 of this service bulletin,'' this AD requires compliance
within the specified compliance time as of August 5, 2010 (the
effective date of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010)).
(8) Where Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011, specifies a compliance time ``after the date on
Revision 3 of this service bulletin,'' or ``after the date on
Revision 4 of this service bulletin,'' this AD requires compliance
within the specified compliance time ``after the effective date of
this AD.''
(n) Optional Terminating Modification
Accomplishing the modification of the bulkhead at BS 2598 in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 747-53A2837, dated July 13, 2012, terminates the
requirements of paragraphs (g), (h), (i), (j), (k), and (l) of this
AD, except where Boeing Alert Service Bulletin 747-53A2837, dated
July 13, 2012, specifies to contact Boeing for appropriate action:
Before further flight, repair the crack using a method approved in
accordance with the procedures specified in paragraph (q) of this
AD.
(o) Terminating Action for Certain Requirements of AD 2010-14-07,
Amendment 39-16352 (75 FR 38001, July 1, 2010)
(1) Accomplishing the inspections, repairs, and modification in
accordance with the Accomplishment Instructions of Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011, is an
acceptable terminating action for the corresponding inspections,
repairs, and modification at the BS 2598 support frame required by
paragraphs (i), (j), (k), (1), (m), (n), (o), (p), (q), (r), (s),
(t), (u), and (v) of AD 2010-14-07, Amendment 39-16352 (75 FR 38001,
July 1, 2010). Where Boeing Service Bulletin 747-
[[Page 23897]]
53A2473, Revision 4, dated December 1, 2011, specifies to contact
Boeing for repair instructions, the repair instructions must be
approved in accordance with the procedures specified in paragraph
(q) of this AD. All provisions of AD 2010-14-07 that are not
specifically referenced in this paragraph remain fully applicable
and must be complied with.
(2) Accomplishing the inspections, repairs, and interim
modification in accordance with Boeing Alert Service Bulletin 747-
53A2427, Revision 7, dated July 19, 2013, is an acceptable
terminating action for the corresponding inspections, repairs and
interim modification at the BS 2598 bulkhead required by paragraphs
(i), (j), (o), (s), (t), (u), and (v) of AD 2010-14-07, Amendment
39-16352 (75 FR 38001, July 1, 2010). Where Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, specifies to
contact Boeing for repair data, the repair data must be approved in
accordance with the procedures specified in paragraph (q) of this
AD. All provisions of AD 2010-14-07 that are not specifically
referenced in this paragraph remain fully applicable and must be
complied with.
(p) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g), (h), (i), and (n)(2) of this AD, if those actions
were performed before the effective date of this AD using Boeing
Alert Service Bulletin 747-53A2427, Revision 6, dated July 14, 2011,
provided that the additional actions added in Boeing Alert Service
Bulletin 747-53A2427, Revision 7, dated July 19, 2013, are done
within the applicable compliance times specified in paragraphs (g),
(h), and (i) of this AD. Boeing Alert Service Bulletin 747-53A2427,
Revision 6, dated July 14, 2011, is not incorporated by reference in
this AD.
(q) 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 (r)(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 required by this AD if it is approved by the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) that has been authorized by the Manager, Seattle ACO, to make
those findings. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) Related portions or applicable paragraphs of AMOCs approved
previously in accordance with AD 2010-14-07, Amendment 39-16352 (75
FR 38001, July 1, 2010), are approved as AMOCs for the corresponding
provisions of paragraphs (g), (h), (i), (j), (k), and (l) of this
AD. All new actions specified in paragraphs (g), (h), (i), (j), (k),
and (l) of this AD that are not identified in a previously approved
AMOC must still be done.
(r) Related Information
(1) For more information about this AD, contact Nathan Weigand,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6428;
fax: 425-917-6590; email: nathan.p.weigand@faa.gov.
(2) Service information identified in this AD that is not
incorporated by reference in this AD may be viewed at the addresses
specified in paragraphs (s)(3) and (s)(4) of this AD.
(s) 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 Alert Service Bulletin 747-53A2427, Revision 7, dated
July 19, 2013.
(ii) Boeing Service Bulletin 747-53A2473, Revision 4, dated
December 1, 2011.
(iii) Boeing Alert Service Bulletin 747-53A2837, dated July 13,
2012.
(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 March 17, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-07339 Filed 4-28-14; 8:45 am]
BILLING CODE 4910-13-P
