Airworthiness Directives; The Boeing Company Airplanes, 41120-41125 [2014-16381]
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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations
(if measured) to the person identified in
paragraph (h)(1) of this AD.
www.archives.gov/federal-register/cfr/ibrlocations.html.
(h) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Rotorcraft Certification
Office, FAA, may approve AMOCs for this
AD. Send your proposal to: Martin Crane,
Aviation Safety Engineer, Rotorcraft
Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth,
Texas 76137; telephone (817) 222–5170;
email 7-AVS-ASW-170@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
Issued in Fort Worth, Texas, on June 16,
2014.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
(i) Additional Information
(1) Metro Aviation, Inc., Alert Service
Bulletin No. MA145–21–004, Revision IR,
dated March 24, 2014, which is not
incorporated by reference, contains
additional information about the subject of
this AD. For service information identified in
this AD, contact Metro Aviation, Inc., 1214
Hawn Ave., Shreveport, LA 71107; phone:
(318) 222–5529; Web site:
metroproductsupport.com. You may review a
copy of the service information at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort
Worth Texas 76137.
(2) STC No. SH3380SW, amended April 16,
2004, may be found on the Internet at, https://
www.regulations.gov in Docket No. FAA–
2014–0395.
RIN 2120–AA64
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(j) Subject
Joint Aircraft Service Component (JASC)
Code: 6500: Tail Rotor Drive.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference 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) Metro Aviation, Inc., Alert Service
Bulletin No. MA145–21B–003, Revision B,
dated December 20, 2013.
(ii) Reserved.
(3) For Metro Aviation, Inc., service
information identified in this AD, contact
Metro Aviation, Inc., 1214 Hawn Ave,
Shreveport, LA 71107; phone: (318) 222–
5529; Web site: metroproductsupport.com.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(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://
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[FR Doc. 2014–16387 Filed 7–14–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0432; Directorate
Identifier 2014–NM–099–AD; Amendment
39–17898; AD 2014–14–03]
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
Examining the AD Docket
We are superseding
Airworthiness Directive (AD) 2014–07–
01, for certain The Boeing Company
Model 747 airplanes. AD 2014–07–01
required repetitive inspections for
cracking in certain bulkhead structure;
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.
This AD clarifies certain paragraph
references and revises a compliance
time. This AD was prompted by a
determination that certain paragraph
references are in error. 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 July 15,
2014.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 3, 2014 (79 FR 23893, April
29, 2014).
We must receive any comments on
this AD by August 29, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
SUMMARY:
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• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
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.
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0432; 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 street address for
the Docket Office (phone: 800–647–
5527) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
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
On March 17, 2014, we issued AD
2014–07–01, Amendment 39–17815 (79
FR 23893, April 29, 2014), for certain
The Boeing Company Model 747
airplanes. AD 2014–07–01 required
repetitive inspections, including postrepair and post-modification
inspections, for cracking in the
bulkhead structure at body station (BS)
2598; certain one-time inspections of
certain fasteners and support frame
modifications on certain airplanes;
related investigative and corrective
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actions, if necessary; and an interim
modification that would terminate
certain repetitive inspections.
AD 2014–07–01, Amendment 39–
17815 (79 FR 23893, April 29, 2014),
resulted from 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.
We issued AD 2014–07–01 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.
Actions Since AD 2014–07–01,
Amendment 39–17815 (79 FR 23893,
April 29, 2014), Was Issued
Paragraph (o)(1) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893,
April 29, 2014), terminated the actions
in certain paragraphs of AD 2010–14–
07, Amendment 39–16352 (75 FR
38001, July 1, 2010). AD 2014–07–01,
however, incorrectly terminated
‘‘paragraphs (k) and (l),’’ which should
have been ‘‘paragraph (k)(1).’’ Paragraph
(o)(1) of this AD corrects that reference
to ‘‘paragraph (k)(1).’’ All provisions of
AD 2010–14–07 that are not specifically
referenced in paragraph (o)(1) of this AD
remain fully applicable and must be
complied with, including paragraph
(k)(2) of AD 2010–14–07.
We also found an additional incorrect
paragraph reference. The first sentence
of paragraph (p) of AD 2014–07–01
provides credit for the actions required
by paragraphs (g), (h), (i), and (n)(2) of
that AD. Paragraph (n)(2) of AD 2014–
07–01 does not exist. The text of
paragraph (p) of this AD has been
revised to refer to paragraphs (g), (h),
and (i) of this AD.
We have also clarified that the
airplanes affected by paragraph (i) of
this AD include airplanes on which an
interim modification, aft inner chord
repair, or upper web repair has been
previously accomplished as specified in
Boeing Alert Service Bulletin 747–
53A2427.
Compliance Time Change for Airplanes
in Groups 4 and 5
We have moved the compliance time
specified in paragraph (j) of 2014–07–
01, Amendment 39–17815 (79 FR
23893, April 29, 2014), into new
paragraphs (j)(1) and (j)(2) of this AD.
Paragraph (j)(1) of this AD restates the
compliance times for airplanes in
Groups 1, 2, and 3. Paragraph (j)(2) of
this AD provides a new compliance
time for airplanes in Groups 4 and 5. We
have added a compliance time (grace
period) of ‘‘18 months after the effective
date of this AD’’ for airplanes in Groups
4 and 5. We have determined that this
new grace period will provide an
acceptable level of safety.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
AD Requirements
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
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modification that would terminate
certain repetitive inspections. This AD
provides clarification of certain
paragraph references and revises a
compliance time.
FAA’s Justification and Determination
of the Effective Date
Since this AD merely corrects
incorrect paragraph references and
includes a relieving grace period for
certain airplanes, notice and
opportunity for public comment before
issuing this AD are unnecessary.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2014–0432; Directorate Identifier 2014–
NM–099–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this AD. We will consider all
comments received by the closing date
and may amend this AD because of
those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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
Action
Bulkhead (support frame) inspection.
Support frame modification .....
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Support frame upper corner
fastener inspection.
Support frame post-modification/post repair inspection.
Labor cost
15:12 Jul 14, 2014
Jkt 232001
Cost per product
Cost on U.S. operators
$0
$4,165 per inspection cycle ....
$766,360 per inspection cycle.
0
$26,775 ...................................
Up to $4,926,600.
0
$1,360 .....................................
Up to $250,240.
0
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.
200 work hours × $85 per
hour = $17,000.
We estimate the following costs to do
any necessary interim modification that
would be required based on the results
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Parts cost
$17,000 ...................................
$3,128,000.
of the inspections of the bulkhead
specified in paragraph (g) of this AD.
We have no way of determining the
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number of aircraft that might need this
interim modification:
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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Interim modification ......................................................
4 work-hours × $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.
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Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (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)
2014–07–01, Amendment 39–17815 (79
FR 23893, April 29, 2014) and adding
the following new AD:
■
2014–14–03 The Boeing Company:
Amendment 39–17898; Docket No.
FAA–2014–0432; Directorate Identifier
2014–NM–099–AD.
(a) Effective Date
This AD is effective July 15, 2014.
(b) Affected ADs
This AD supersedes AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014).
(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.
List of Subjects in 14 CFR Part 39
(f) Compliance
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Inspections of the Bulkhead
(Support Frame) With No Changes
This paragraph restates the actions
required by paragraph (g) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with no changes. 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 openhole 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 openhole 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) Retained Interim Modification With No
Changes
This paragraph restates the actions
required by paragraph (h) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with no changes. 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
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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.
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(i) Retained Post-Repair Inspection or PostInterim Modification Inspection With a
Clarification
This paragraph restates the actions
required by paragraph (i) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with a clarification of the affected
airplanes. 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, or has been
previously accomplished as specified in
Boeing Alert Service Bulletin 747–53A2427:
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) Retained Bulkhead (Support Frame)
Modification and Inspections With a Revised
Compliance Time
This paragraph restates the actions
required by paragraph (j) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with a revised compliance time.
For airplanes on which the bulkhead
(support frame) modification, as specified in
Boeing Service Bulletin 747–53A2473 has
not been done as of June 3, 2014 (the
effective date of AD 2014–07–01): At the
applicable time specified in paragraph (j)(1)
or (j)(2) of this AD, 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,
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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.
(1) For Groups 1, 2, and 3 airplanes
identified in Boeing Service Bulletin 747–
53A2473, Revision 4, dated December 1,
2011: At the time specified in table 2 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Service Bulletin 747–53A2473, Revision 4,
dated December 1, 2011.
(2) For Groups 4 and 5 airplanes identified
in Boeing Service Bulletin 747–53A2473,
Revision 4, dated December 1, 2011: At the
earlier of the times specified in paragraphs
(j)(2)(i) and (j)(2)(ii) of this AD,
(i) Before the accumulation of 20,000 total
flight cycles or within 18 months after
August 5, 2010 (the effective date of AD
2010–14–07, Amendment 39–16352 (75 FR
38001, July 1, 2010), whichever occurs later.
(ii) Before the accumulation of 12,000 total
flight cycles or within 18 months after the
effective date of this AD, whichever occurs
later.
(k) Retained Post-Modification Inspections
With No Changes
This paragraph restates the actions
required by paragraph (k) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with no changes.
(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
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
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41123
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 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) Retained Post-Modification and PostRepair Inspections With No Changes
This paragraph restates the actions
required by paragraph (l) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with no changes. For airplanes on
which cracking was found during a postmodification 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–
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wreier-aviles on DSK5TPTVN1PROD with RULES
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) Retained Exceptions to Service
Information With No Changes
This paragraph restates the exceptions
specified in paragraph (m) of AD 2014–07–
01, Amendment 39–17815 (79 FR 23893,
April 29, 2014), with no changes.
(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 June 3,
2014 (the effective date of AD 2014–07–01
Amendment 39–17815 (79 FR 23893, April
29, 2014)).
(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
VerDate Mar<15>2010
15:12 Jul 14, 2014
Jkt 232001
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
June 3, 2014 (the effective date of AD 2010–
14–07, Amendment 39–17815 (79 FR 23893,
April 29, 2014)).
(n) Retained Optional Terminating
Modification With No Changes
This paragraph restates the actions
required by paragraph (n) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with no changes. 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) Retained Terminating Action for Certain
Requirements of AD 2010–14–07,
Amendment 39–16352 (75 FR 38001, July 1,
2010), With Revised Terminating Action
This paragraph restates the terminating
actions specified in paragraph (o) of AD
2014–07–01, Amendment 39–17815 (79 FR
23893, April 29, 2014), with revised
terminating action within paragraph (o)(1) of
this AD.
(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–
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, including paragraph (k)(2) of
AD 2010–14–07.
(2) Accomplishing the inspections, repairs,
and interim modification in accordance with
Boeing Alert Service Bulletin 747–53A2427,
PO 00000
Frm 00040
Fmt 4700
Sfmt 4700
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) Retained Credit for Previous Actions
With Change to Paragraph Reference
This paragraph restates the credit specified
in paragraph (p) of AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), with a change to a paragraph
reference. This paragraph provides credit for
the actions required by paragraphs (g), (h),
and (i) of this AD, if those actions were
performed before June 3, 2014 (the effective
date of AD 2014–07–01) 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
for 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
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(g), (h), (i), (j), (k), and (l) of this AD that are
not identified in a previously approved
AMOC must still be done.
(5) AMOCs approved for AD 2014–07–01,
Amendment 39–17815 (79 FR 23893, April
29, 2014), are approved as AMOCs for the
corresponding provisions of this AD.
(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)(4) and (s)(5) of
this AD.
wreier-aviles on DSK5TPTVN1PROD with RULES
(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.
(3) The following service information was
approved for IBR on June 3, 2014 (79 FR
23893).
(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.
(4) 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.
(5) 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.
(6) 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
VerDate Mar<15>2010
15:12 Jul 14, 2014
Jkt 232001
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on July 3,
2014.
Dionne Palermo,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–16381 Filed 7–14–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 91 and 135
[Docket No. FAA–2010–0982; Amdt. No(s).
91–330A, 135–129A]
RIN 2120–AJ53
Helicopter Air Ambulance, Commercial
Helicopter, and Part 91 Helicopter
Operations; Correction
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; Correction.
AGENCY:
The FAA is correcting a final
rule published on February 21, 2014. In
that rule, the FAA amended its
regulations to revise the helicopter air
ambulance, commercial helicopter, and
general aviation helicopter operating
requirements. This document corrects
errors in the codified text of that
document.
SUMMARY:
DATES:
Effective April 22, 2015.
FOR FURTHER INFORMATION CONTACT:
For
technical questions concerning this
action, contact Andrew C. Pierce, Air
Transportation Division, 135 Air Carrier
Operations Branch, AFS–250, Federal
Aviation Administration, 800
Independence Avenue SW.,
Washington, DC 20591; telephone 202–
267–8238; email andy.pierce@faa.gov.
For legal questions concerning this
action, contact Nancy Sanchez,
PO 00000
Frm 00041
Fmt 4700
Sfmt 4700
41125
Attorney, AGC–220, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC 20591;
telephone 202–267–3073; email
nancy.sanchez@faa.gov.
SUPPLEMENTARY INFORMATION:
Background
On February 21, 2014, the FAA
published a final rule entitled,
‘‘Helicopter Air Ambulance,
Commercial Helicopter, and part 91
Helicopter Operations’’ (79 FR 9932)
(effective date delayed on April 21,
2014, at 79 FR 22012). In that final rule,
the FAA addressed helicopter air
ambulance operations and all
commercial helicopter operations
conducted under part 135. The FAA
also established new weather
minimums for helicopters operating
under part 91 in Class G airspace.
The FAA is correcting § 91.155 and
removing duplicative flight visibility
requirements for part 91 helicopter
operations in Class G airspace. Also, the
FAA is correcting the regulatory text in
§ 135.609 to delineate visual flight rule
operations and instrument flight rules
operations. Finally, the agency is
correcting the regulatory text in
§ 135.621(b) and clarifying the intended
list of topics that must be included in
the certificate holder’s FAA-approved
medical personnel training program.
Corrections
In FR Doc. 35, beginning on page
9932, in the Federal Register of
February 21, 2014, make the following
corrections:
Corrections to Regulatory Text
1. On page 9973, in § 91.155, revise
the entry ‘‘For helicopters: Day’’ in the
table in paragraph (a) to read as follows:
■
§ 91.155
Basic VFR weather minimums.
(a) * * *
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]]>Agencies
[Federal Register Volume 79, Number 135 (Tuesday, July 15, 2014)]
[Rules and Regulations]
[Pages 41120-41125]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-16381]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD;
Amendment 39-17898; AD 2014-14-03]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-07-01,
for certain The Boeing Company Model 747 airplanes. AD 2014-07-01
required repetitive inspections for cracking in certain bulkhead
structure; 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. This AD clarifies
certain paragraph references and revises a compliance time. This AD was
prompted by a determination that certain paragraph references are in
error. 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 July 15, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 3, 2014
(79 FR 23893, April 29, 2014).
We must receive any comments on this AD by August 29, 2014.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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-2014-
0432; 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 street address for the Docket Office (phone:
800-647-5527) is in the ADDRESSES section. Comments will be available
in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: 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
On March 17, 2014, we issued AD 2014-07-01, Amendment 39-17815 (79
FR 23893, April 29, 2014), for certain The Boeing Company Model 747
airplanes. AD 2014-07-01 required repetitive inspections, including
post-repair and post-modification inspections, for cracking in the
bulkhead structure at body station (BS) 2598; certain one-time
inspections of certain fasteners and support frame modifications on
certain airplanes; related investigative and corrective
[[Page 41121]]
actions, if necessary; and an interim modification that would terminate
certain repetitive inspections.
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
resulted from 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. We
issued AD 2014-07-01 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.
Actions Since AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29,
2014), Was Issued
Paragraph (o)(1) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893,
April 29, 2014), terminated the actions in certain paragraphs of AD
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010). AD 2014-07-
01, however, incorrectly terminated ``paragraphs (k) and (l),'' which
should have been ``paragraph (k)(1).'' Paragraph (o)(1) of this AD
corrects that reference to ``paragraph (k)(1).'' All provisions of AD
2010-14-07 that are not specifically referenced in paragraph (o)(1) of
this AD remain fully applicable and must be complied with, including
paragraph (k)(2) of AD 2010-14-07.
We also found an additional incorrect paragraph reference. The
first sentence of paragraph (p) of AD 2014-07-01 provides credit for
the actions required by paragraphs (g), (h), (i), and (n)(2) of that
AD. Paragraph (n)(2) of AD 2014-07-01 does not exist. The text of
paragraph (p) of this AD has been revised to refer to paragraphs (g),
(h), and (i) of this AD.
We have also clarified that the airplanes affected by paragraph (i)
of this AD include airplanes on which an interim modification, aft
inner chord repair, or upper web repair has been previously
accomplished as specified in Boeing Alert Service Bulletin 747-53A2427.
Compliance Time Change for Airplanes in Groups 4 and 5
We have moved the compliance time specified in paragraph (j) of
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014), into new
paragraphs (j)(1) and (j)(2) of this AD. Paragraph (j)(1) of this AD
restates the compliance times for airplanes in Groups 1, 2, and 3.
Paragraph (j)(2) of this AD provides a new compliance time for
airplanes in Groups 4 and 5. We have added a compliance time (grace
period) of ``18 months after the effective date of this AD'' for
airplanes in Groups 4 and 5. We have determined that this new grace
period will provide an acceptable level of safety.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
AD Requirements
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. This AD provides
clarification of certain paragraph references and revises a compliance
time.
FAA's Justification and Determination of the Effective Date
Since this AD merely corrects incorrect paragraph references and
includes a relieving grace period for certain airplanes, notice and
opportunity for public comment before issuing this AD are unnecessary.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
``Docket No. FAA-2014-0432; Directorate Identifier 2014-NM-099-AD'' at
the beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of this
AD. We will consider all comments received by the closing date and may
amend this AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Bulkhead (support frame) 49 work-hours x $85 $0 $4,165 per $766,360 per
inspection. per hour = $4,165 inspection cycle. inspection cycle.
per inspection
cycle.
Support frame modification....... 315 work-hours x $85 0 $26,775............. Up to $4,926,600.
per hour = $26,775.
Support frame upper corner 16 work-hours x $85 0 $1,360.............. Up to $250,240.
fastener inspection. per hour = $1,360.
Support frame post-modification/ 200 work hours x $85 0 $17,000............. $3,128,000.
post repair inspection. per hour = $17,000.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary interim
modification that would be required based on the results of the
inspections 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:
[[Page 41122]]
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Interim modification......................... 4 work-hours x $85 per hour = $0 $340
$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
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 part 39 of the Federal Aviation
Regulations (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)
2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014) and adding
the following new AD:
2014-14-03 The Boeing Company: Amendment 39-17898; Docket No. FAA-
2014-0432; Directorate Identifier 2014-NM-099-AD.
(a) Effective Date
This AD is effective July 15, 2014.
(b) Affected ADs
This AD supersedes AD 2014-07-01, Amendment 39-17815 (79 FR
23893, April 29, 2014).
(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) Retained Inspections of the Bulkhead (Support Frame) With No
Changes
This paragraph restates the actions required by paragraph (g) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. 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) Retained Interim Modification With No Changes
This paragraph restates the actions required by paragraph (h) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. 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
[[Page 41123]]
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) Retained Post-Repair Inspection or Post-Interim Modification
Inspection With a Clarification
This paragraph restates the actions required by paragraph (i) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a clarification of the affected airplanes. 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, or has been previously accomplished as specified in Boeing Alert
Service Bulletin 747-53A2427: 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) Retained Bulkhead (Support Frame) Modification and Inspections With
a Revised Compliance Time
This paragraph restates the actions required by paragraph (j) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a revised compliance time. For airplanes on which the bulkhead
(support frame) modification, as specified in Boeing Service
Bulletin 747-53A2473 has not been done as of June 3, 2014 (the
effective date of AD 2014-07-01): At the applicable time specified
in paragraph (j)(1) or (j)(2) of this AD, 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.
(1) For Groups 1, 2, and 3 airplanes identified in Boeing
Service Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At
the time specified in table 2 of paragraph 1.E., ``Compliance,'' of
Boeing Service Bulletin 747-53A2473, Revision 4, dated December 1,
2011.
(2) For Groups 4 and 5 airplanes identified in Boeing Service
Bulletin 747-53A2473, Revision 4, dated December 1, 2011: At the
earlier of the times specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD,
(i) Before the accumulation of 20,000 total flight cycles or
within 18 months after August 5, 2010 (the effective date of AD
2010-14-07, Amendment 39-16352 (75 FR 38001, July 1, 2010),
whichever occurs later.
(ii) Before the accumulation of 12,000 total flight cycles or
within 18 months after the effective date of this AD, whichever
occurs later.
(k) Retained Post-Modification Inspections With No Changes
This paragraph restates the actions required by paragraph (k) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes.
(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 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) Retained Post-Modification and Post-Repair Inspections With No
Changes
This paragraph restates the actions required by paragraph (l) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. 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-
[[Page 41124]]
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) Retained Exceptions to Service Information With No Changes
This paragraph restates the exceptions specified in paragraph
(m) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29,
2014), with no changes.
(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 June 3, 2014
(the effective date of AD 2014-07-01 Amendment 39-17815 (79 FR
23893, April 29, 2014)).
(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 June 3, 2014 (the
effective date of AD 2010-14-07, Amendment 39-17815 (79 FR 23893,
April 29, 2014)).
(n) Retained Optional Terminating Modification With No Changes
This paragraph restates the actions required by paragraph (n) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with no changes. 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) Retained Terminating Action for Certain Requirements of AD 2010-14-
07, Amendment 39-16352 (75 FR 38001, July 1, 2010), With Revised
Terminating Action
This paragraph restates the terminating actions specified in
paragraph (o) of AD 2014-07-01, Amendment 39-17815 (79 FR 23893,
April 29, 2014), with revised terminating action within paragraph
(o)(1) of this AD.
(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 747-53A2473, 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,
including paragraph (k)(2) of AD 2010-14-07.
(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) Retained Credit for Previous Actions With Change to Paragraph
Reference
This paragraph restates the credit specified in paragraph (p) of
AD 2014-07-01, Amendment 39-17815 (79 FR 23893, April 29, 2014),
with a change to a paragraph reference. This paragraph provides
credit for the actions required by paragraphs (g), (h), and (i) of
this AD, if those actions were performed before June 3, 2014 (the
effective date of AD 2014-07-01) 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 for 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
[[Page 41125]]
(g), (h), (i), (j), (k), and (l) of this AD that are not identified
in a previously approved AMOC must still be done.
(5) AMOCs approved for AD 2014-07-01, Amendment 39-17815 (79 FR
23893, April 29, 2014), are approved as AMOCs for the corresponding
provisions of this AD.
(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)(4) and (s)(5) 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.
(3) The following service information was approved for IBR on
June 3, 2014 (79 FR 23893).
(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.
(4) 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.
(5) 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.
(6) 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 July 3, 2014.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-16381 Filed 7-14-14; 8:45 am]
BILLING CODE 4910-13-P
