Airworthiness Directives; The Boeing Company Airplanes, 45453-45457 [2015-18559]
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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
• Email: ConventionalCooking
Products2014STD0005@ee.doe.gov.
Include the docket number EERE–2014–
BT–STD–0005 in the subject line of the
message.
• Mail: Ms. Brenda Edwards, U.S.
Department of Energy, Building
Technologies Program, Mailstop EE–5B,
Notice of Proposed Rulemaking for
Energy Conservation Standards for
Residential Conventional Ovens, Docket
No. EERE–2014–BT–STD–0014, 1000
Independence Avenue SW.,
Washington, DC 20585–0121. If
possible, please submit all items on a
CD. It is not necessary to include
printed copies.
• Hand Delivery/Courier: Ms. Brenda
Edwards, U.S. Department of Energy,
Building Technologies Program, 950
L’Enfant Plaza SW., Suite 600,
Washington, DC 20024. Telephone (202)
586–2945. If possible, please submit all
items on a CD, in which case it is not
necessary to include printed copies.
Instructions: All submissions received
must include the agency name and
docket number for this rulemaking. No
telefacsimiles (faxes) will be accepted.
Docket: The docket is available for
review at www.regulations.gov,
including Federal Register notices,
comments, and other supporting
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not all documents listed in the index
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A link to the docket Web page can be
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#!documentDetail;D=EERE-2014-BTSTD-0005-0014. This Web page contains
a link to the docket for this notice on the
regulation.gov site. The
www.regulations.gov Web page contains
instructions on how to access all
documents in the docket, including
public comments.
FOR FURTHER INFORMATION CONTACT:
Mr. John Cymbalsky, U.S. Department of
Energy, Office of Energy Efficiency
and Renewable Energy, Building
Technologies Program, EE–2J, 1000
Independence Avenue SW.,
Washington, DC 20585–0121.
Telephone: (202) 287–1692. Email:
kitchen_ranges_and_ovens@
ee.doe.gov.
Ms. Celia Sher, U.S. Department of
Energy, Office of the General Counsel,
GC–33, 1000 Independence Avenue
SW., Washington, DC 20585–0121.
Telephone: (202) 287–6122. Email:
Celia.Sher@hq.doe.gov.
SUPPLEMENTARY INFORMATION: On June
10, 2015, DOE published a notice of
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proposed rulemaking (NOPR) and
public meeting in the Federal Register
that proposed new and amended energy
conservation standards for residential
conventional ovens. 80 FR 33030. The
NOPR requested comment from the
public on the proposed standards,
associated analyses, and results, and
provided for the written submission of
comments by August 10, 2015. The
Association of Home Appliance
Manufacturers (AHAM) requested that
DOE extend the comment period by 60
days so that manufacturers can obtain
sufficient data to fully analyze DOE’s
proposed rule according to the
conventional oven test procedure final
rule that was published on July 2, 2015.
80 FR 37954. Because there are
currently no performance based energy
conservation standards, AHAM noted
that manufacturers do not conduct
regular energy tests on conventional
ovens. AHAM further stated that by
allowing additional time for
manufacturers (and other stakeholders
who wish to conduct testing) to test
their products, manufacturers will be
able to provide key data to support
DOE’s analysis.
Based on AHAM’s request, DOE
determines that a 30 day extension of
the public comment period is
appropriate to allow interested parties
additional time to submit comments.
DOE notes that it issued and made
available a pre-publication version of
the conventional oven test procedure
final rule on June 9, 2015. Based on
DOE’s testing experience, extending the
comment period by 30 days for a 90 day
total period should be sufficient time for
manufacturers to conduct testing using
the new oven test procedure and
aggregate results. DOE will consider any
comments received by midnight of
September 9, 2015 to be timely
submitted.
Issued in Washington, DC, on July 23,
2015.
Kathleen B. Hogan,
Deputy Assistant Secretary for Energy
Efficiency, Energy Efficiency and Renewable
Energy.
[FR Doc. 2015–18687 Filed 7–29–15; 8:45 am]
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45453
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2965; Directorate
Identifier 2014–NM–227–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2012–17–
13, which applies to certain The Boeing
Company Model 707 airplanes, and
Model 720 and 720B series airplanes.
For certain airplanes, AD 2012–17–13
required using redefined flight cycle
counts; determining the type of material
of the horizontal stabilizer, rear spar,
and upper and lower chords on the
inboard and outboard ends of the rear
spar; repetitively inspecting for cracking
of the horizontal stabilizer components;
and repairing or replacing the chord, or
modifying chord segments made of 7079
aluminum, if necessary. For all
airplanes, AD 2012–17–13 required
inspecting certain structurally
significant items, and repairing
discrepancies if necessary. Since we
issued AD 2012–17–13, we have
determined that all chord segments
made of 7079 aluminum must be
replaced with new, improved chord
segments made of 7075 aluminum. This
proposed AD would add a requirement
to replace all chord segments made of
7079 aluminum with new, improved
chord segments made of 7075
aluminum. We are proposing this AD to
detect and correct stress corrosion and
potential early fatigue cracking in the
horizontal stabilizer, which could result
in reduced structural integrity of the
horizontal stabilizer.
DATES: We must receive comments on
this proposed AD by September 14,
2015.
SUMMARY:
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.
ADDRESSES:
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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, 3855
Lakewood Boulevard, MC D800–0019,
Long Beach, CA 90846–0001; telephone
206–544–5000, extension 2; fax 206–
766–5683; 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.
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Comments Invited
Discussion
On August 24, 2012, we issued AD
2012–17–13, Amendment 39–17176 (77
FR 55681, September 11, 2012), for
certain The Boeing Company Model 707
airplanes, and Model 720 and 720B
series airplanes. For certain airplanes,
AD 2012–17–13 required using
redefined flight cycle counts,
determining the type of material of the
horizontal stabilizer, rear spar, and
upper and lower chords on the inboard
and outboard ends of the rear spar;
repetitively inspecting for cracking of
the horizontal stabilizer components;
and repairing or replacing the chord, or
modifying chord segments made from
7079 aluminum, if necessary. For all
airplanes, AD 2012–17–13 required
inspecting certain structurally
significant items, and repairing
discrepancies if necessary. AD 2012–
17–13 resulted from reports of stress
corrosion cracking in the chord
segments made from 7079 aluminum in
the horizontal stabilizer rear spar, and
potential early fatigue cracking in the
chord segments made from 7075
aluminum. We issued AD 2012–17–13
to detect and correct stress corrosion
and potential early fatigue cracking in
the horizontal stabilizer, which could
compromise the structural integrity of
the stabilizer.
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2015–2965; Directorate Identifier
2014–NM–227–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
Actions Since AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), Was Issued
The preamble to AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), explained that we
considered the requirements ‘‘interim
action’’ and were considering further
rulemaking. We now have determined
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–2015–
2965; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Chandra Ramdoss, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office
(ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone:
562–627–5239; fax: 562–627–5210;
email: chandraduth.ramdoss@faa.gov.
SUPPLEMENTARY INFORMATION:
that it is necessary to initiate further
rulemaking to continue to require the
repetitive inspections required by AD
2012–17–13, and to add a requirement
for replacement of all chord segments
made of 7079 aluminum with new
chord segments made of 7075
aluminum. This proposed AD follows
from that determination.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated
October 10, 2014. The service
information describes procedures for
incorporating a new cycle counting
procedure, determining the material for
the horizontal stabilizer rear spar chord
segment, inspecting for stress corrosion
cracking and fatigue cracking, repair,
and replacing all chord segments made
of 7079 aluminum with new, improved
chord segments made of 7075
aluminum. This service information is
reasonably available because the
interested parties have access to it
through their normal course of business
or by the means identified in the
ADDRESSES section of this NPRM.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of these same
type designs.
Proposed AD Requirements
This proposed AD would retain all
requirements of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012). This proposed AD
would also add a requirement to replace
all chord segments made of 7079
aluminum with new chord segments
made of 7075 aluminum. This
replacement would not terminate the
repetitive inspections required by AD
2012–17–13.
Costs of Compliance
We estimate that this proposed AD
affects 10 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
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TABLE—ESTIMATED COSTS
Action
Work hours
Parts
Cost per product
Fleet cost
Retained inspections from AD 2012–
17–13, Amendment 39–17176 (77
FR 55681, September 11, 2012).
Up to 32 work-hours X $85 per hour =
up to $2,720 per inspection cycle.
$0 ..........................
Up to $2,720 per
inspection cycle.
Up to $27,200 per
inspection cycle
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TABLE—ESTIMATED COSTS—Continued
Action
Work hours
Parts
Replacement [new action] ....................
500 work-hours X $85 per work-hour
= $42,500.
Cost per product
Up to $228,000
per chord.
Up to $2,322,500
(up to 10 chords
per airplane) 1.
Fleet cost
Up to
$23,225,000 2
1 The parts for the modification could cost up to $2.28 million per airplane, depending on whether only one operator is ordering the parts or
multiple operators. The parts cost will go down if multiple operators order parts at the same time.
2 The number of chords which must be replaced on each specific airplane varies.
Authority for This Rulemaking
The Proposed Amendment
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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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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)
2012–17–13, Amendment 39–17176 (77
FR 55681, September 11, 2012), and
adding the following new AD:
■
The Boeing Company: Docket No. FAA–
2015–2965; Directorate Identifier 2014–
NM–227–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by September 14, 2015.
(b) Affected ADs
This AD replaces AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012).
(c) Applicability
This AD applies to The Boeing Company
airplanes, certificated in any category;
identified in paragraphs (c)(1) and (c)(2) of
this AD.
(1) Model 707 airplanes identified in
Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014.
(2) Model 720 and 720B series airplanes
identified in Boeing 707 Alert Service
Bulletin A3516, dated April 4, 2008.
(d) Subject
Air Transport Association (ATA) of
America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a determination
that all chord segments made of 7079
aluminum must be replaced with new,
improved chord segments made of 7075
aluminum. We are issuing this AD to detect
and correct stress corrosion and potential
early fatigue cracking in the horizontal
stabilizer, which could result in reduced
structural integrity of the horizontal
stabilizer.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Flight Cycle Counting
Procedure, With Revised Service
Information
This paragraph restates the requirements of
paragraph (g) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. Flight cycles, as used in this
AD, must be counted as defined in the
service information identified in paragraph
(g)(1), (g)(2), or (g)(3) of this AD.
(1) Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007 (for Model
airplanes).
(2) Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014
(for Model airplanes).
(3) Boeing 707 Alert Service Bulletin
A3516, dated April 4, 2008 (for Model
airplanes, and Model 720 and 720B series
airplanes).
(h) Retained Determination of Material of
the Components of the Horizontal Stabilizer,
With Revised Service Information
This paragraph restates the actions
required by paragraph (h) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. For airplanes identified in
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014: At the earlier of the
times specified in paragraphs (h)(1) and
(h)(2) of this AD, determine the type of
material of the horizontal stabilizer, rear spar,
upper chords, and lower chords on the
inboard and outboard ends of the rear spar,
in accordance with Part 2 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014.
(1) Within 180 days after October 16, 2012
(the effective date of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012)).
(2) Before further flight after any horizontal
stabilizer is replaced after October 16, 2012.
(i) Retained Repetitive Inspections of 7075
Aluminum Components, With Revised
Service Information
This paragraph restates the actions
required by paragraph (i) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
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information. For airplanes with horizontal
stabilizer components made from 7075
aluminum, as determined during the
inspection required by paragraph (h) of this
AD: Within 180 days after October 16, 2012
(the effective date of AD 2012–17–13), and
before further flight after any replacement of
the horizontal stabilizer, do a special detailed
inspection for cracking of the upper chord on
the inboard end of the rear spar on both the
left and right side horizontal stabilizers, from
stabilizer station –13.179 to 92.55, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014. Repeat the inspections
thereafter at intervals not to exceed 500 flight
cycles, and before further flight after any
replacement of the horizontal stabilizer,
except as provided by paragraph (j) of this
AD. If any cracking is found, before further
flight, either repair the cracking in
accordance with Part 3 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014, except as required by
paragraph (n) of this AD; or replace the chord
with a new chord, in accordance with Part
6 of the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014.
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(j) Retained Repetitive Inspections on
Airplanes With Replaced Chord, With
Revised Service Information
This paragraph restates the actions
required by paragraph (j) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. For airplanes on which the
chord is replaced with a new chord in
accordance with Part 6 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014: Within 4,000 flight cycles
after the chord replacement, do the
inspections required by paragraph (i) of this
AD, and repeat the inspections thereafter at
the times specified in paragraph (i) of this
AD.
(k) Retained Repetitive Inspections of 7079
Aluminum Components, With Revised
Service Information
This paragraph restates the actions
required by paragraph (k) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. For airplanes with horizontal
stabilizers that have components of the
chords of the rear spar made from 7079
aluminum, as determined during the
inspection required by paragraph (h) of this
AD: Within 180 days after October 16, 2012
(the effective date of AD 2012–17–13), do the
actions required by paragraphs (k)(1), (k)(2),
and (k)(3) of this AD, and repeat those
actions at the applicable intervals specified
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in paragraphs (k)(1), (k)(2), and (k)(3) of this
AD.
(1) Do a special detailed inspection for
cracking of the upper chord of the inboard
side of the rear spar of both the -left and
right-side horizontal stabilizers from
stabilizer station –13.179 to 92.55, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014. Repeat the inspection
thereafter at intervals not to exceed 250 flight
cycles or 180 days, whichever occurs first. If
any cracking is found during any inspection
required by this paragraph, before further
flight, either repair the cracking, in
accordance with Part 3 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014, except as required by
paragraph (n) of this AD; or replace the chord
with a new chord, in accordance with Part
6 of the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014.
(2) Do a high frequency eddy current
inspection for cracking of the web flanges of
the upper and lower chords of the rear spar
in the left and right side horizontal stabilizers
from stabilizer stations 92.55 to 272.55, in
accordance with Part 4 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014. Repeat the inspection
thereafter at intervals not to exceed 1,000
flight cycles or 180 days, whichever occurs
first. If any cracking is found during any
inspection required by this paragraph, before
further flight, do the actions specified in
paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
(i) Determine whether the cracking meets
the limits specified in Part 4 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014, and whether a previous
repair has been done; determine if all 7079
upper and lower chord segments installed on
the horizontal stabilizer have had the Part II,
Group 1, Preventative Modification specified
in Boeing Service Bulletin 3356 done; and do
all applicable repairs and modifications, in
accordance with the Accomplishment
Instructions of Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or
Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014. Do the
actions required by this paragraph in
accordance with Part 4 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014, except as required by
paragraph (n) of this AD. Do all applicable
repairs and modifications before further
flight.
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(ii) Replace the chord with a new chord,
in accordance with Part 6 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014.
(3) Do low frequency eddy current (LFEC)
inspections for cracking of the forward skin
flanges of the upper and lower chords of the
rear spar in the left and right side horizontal
stabilizers from stabilizer stations –13.179 to
272.55 (for lower chords) and 92.55 to 272.55
(for upper chords), in accordance with Part
5 of the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014. Repeat the
inspections thereafter at intervals not to
exceed 1,000 flight cycles or 180 days,
whichever occurs first. If any cracking is
found during any inspection required by this
paragraph, before further flight, do the
actions specified in either paragraph (k)(3)(i)
or paragraph (k)(3)(ii) of this AD.
(i) Repair any cracking, determine whether
all 7079 upper and lower chord segments
installed on the horizontal stabilizer have
had the Part II—Preventative Modification
specified in Boeing Service Bulletin 3381
done, and do all applicable modifications, in
accordance with the Accomplishment
Instructions of Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or
Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014. Do the
actions required by this paragraph in
accordance with Part 5 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014, except as required by
paragraph (n) of this AD. Do all applicable
modifications before further flight.
(ii) Replace the chord with a new chord,
in accordance with Part 6 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007; or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014.
(l) Retained Modification/Chord
Replacement, With Revised Service
Information
This paragraph restates the actions
required by paragraph (l) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. For airplanes identified in
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014, with horizontal
stabilizers that have rear spar chord
components made from 7079 aluminum and
have not had embodied the modification of
Part II of Boeing Service Bulletin 3381, dated
July 25, 1980, or Boeing Service Bulletin
3381, Revision 1, dated July 31, 1981: Before
further flight after determining the type of
material in accordance with paragraph (h) of
this AD, modify all 7079 chord segments
installed on the horizontal stabilizer, in
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30JYP1
Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules
accordance with Part 5 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014; or replace the chord, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated
October 10, 2014.
(m) Retained Supplemental Structural
Inspection Document Inspections
This paragraph restates the actions
required by paragraph (m) of AD 2012–17–
13, Amendment 39–17176 (77 FR 55681,
September 11, 2012). For all airplanes:
Within 180 days or 1,000 flight cycles after
October 16, 2012 (the effective date of AD
2012–17–13), whichever occurs first, do the
inspections of the applicable structurally
significant items specified in and in
accordance with the Accomplishment
Instructions of Boeing 707 Alert Service
Bulletin A3516, dated April 4, 2008. If any
cracking is found, before further flight, repair
in accordance with the procedures specified
in paragraph (r) of this AD. The inspections
required by AD 85–12–01 R1, Amendment
39–5439 (51 FR 36002, October 8, 1986), are
still required, except, as of October 16, 2012
(the effective date of AD 2012–17–13), the
flight-cycle interval for the repetitive
inspections specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing 707 Alert Service
Bulletin A3516, dated April 4, 2008, must be
counted in accordance with the requirements
of paragraph (g) of this AD.
Lhorne on DSK7TPTVN1PROD with PROPOSALS
(n) Retained Exception to Certain Service
Information: Contacting FAA for Crack
Repair
This paragraph restates the actions
required by paragraph (n) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. If any cracking is found during
any inspection required by this AD, and
Boeing 707 Alert Service Bulletin A3515,
dated December 19, 2007, or Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014, specifies to contact
Boeing for appropriate action: Before further
flight, repair the cracking using a method
approved in accordance with the procedures
specified in paragraph (r) of this AD.
(o) Retained Exception to Certain Service
Information: Nondestructive Test
Compliance Procedures
This paragraph restates the requirements of
paragraph (o) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. Where Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or
Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014, specifies
that operators ‘‘refer to’’ nondestructive test
(NDT) procedures, the procedures must be
done in accordance with the service
information identified in paragraphs (o)(1),
(o)(2), and (o)(3) of this AD, as applicable.
(1) Figure 20, ‘‘Electrical Conductivity
Measurement for Aluminum,’’ of Subject 51–
VerDate Sep<11>2014
13:52 Jul 29, 2015
Jkt 235001
00–00, ‘‘Structures-General,’’ of Part 6—Eddy
Current, of the Boeing 707/720
Nondestructive Test Manual, Document D6–
48023, Revision 118, dated July 15, 2011.
(2) Subject 55–10–07, ‘‘Horizontal
Stabilizer,’’ of Part 6—Eddy Current, of the
Boeing 707/720 Nondestructive Test Manual,
Document D6–48023, Revision 118, dated
July 15, 2011.
(3) Subject 51–01–00, ‘‘Orientation and
Preparation for Testing’’ of Part 1—General,
of the Boeing 707/720 Nondestructive Test
Manual, Document D6–48023, Revision 118,
dated July 15, 2011.
(p) Retained Parts Installation Prohibition
As of October 16, 2012 (the effective date
of AD 2012–17–13, Amendment 39–17176
(77 FR 55681, September 11, 2012)), no
person may install any horizontal stabilizer
assembly with any chord segment having a
part number other than that identified in
paragraph 2.C.2. of Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or
Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014, on any
airplane.
(q) New Replacement of 7079 Aluminum
Components
Within 48 months after the effective date
of this AD: Replace all 7079 aluminum chord
segments of the upper and lower chords
installed on the horizontal stabilizer with
7075 aluminum chord segments, in
accordance with Part 6 of the
Accomplishment Instructions of Boeing 707
Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014. Within 4,000 flight
cycles after accomplishing the replacements
required by this paragraph, repeat the
inspection required by paragraph (j) of this
AD; and repeat the inspection thereafter at
intervals not to exceed 500 flight cycles, and
before further flight after any replacement of
the horizontal stabilizer.
(r) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles 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 (s)(1) of this AD. Information may
be emailed to: 9-ANM-LAACO-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, Los Angeles
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.
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
45457
(4) AMOCs approved for AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), are approved as
AMOCs for the corresponding provisions of
this AD.
(s) Related Information
(1) For more information about this AD,
contact Chandra Ramdoss, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5239; fax: 562–627–5210; email:
chandraduth.ramdoss@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2; fax
206–766–5683; 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.
Issued in Renton, Washington, on July 16,
2015.
Suzanne Masterson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2015–18559 Filed 7–29–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2964; Directorate
Identifier 2014–NM–206–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A319, A320, and A321
series airplanes. This proposed AD is
intended to complete certain mandated
programs intended to support the
airplane reaching its limit of validity
(LOV) of the engineering data that
support the established structural
maintenance program. This proposed
AD would require reinforcing the
forward pressure bulkhead at a certain
stringer on both the left-hand and righthand sides, and related investigative
and corrective actions if necessary. We
are proposing this AD to prevent fatigue
cracking of the forward pressure
SUMMARY:
E:\FR\FM\30JYP1.SGM
30JYP1
]]>Agencies
[Federal Register Volume 80, Number 146 (Thursday, July 30, 2015)]
[Proposed Rules]
[Pages 45453-45457]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-18559]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2965; Directorate Identifier 2014-NM-227-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-17-
13, which applies to certain The Boeing Company Model 707 airplanes,
and Model 720 and 720B series airplanes. For certain airplanes, AD
2012-17-13 required using redefined flight cycle counts; determining
the type of material of the horizontal stabilizer, rear spar, and upper
and lower chords on the inboard and outboard ends of the rear spar;
repetitively inspecting for cracking of the horizontal stabilizer
components; and repairing or replacing the chord, or modifying chord
segments made of 7079 aluminum, if necessary. For all airplanes, AD
2012-17-13 required inspecting certain structurally significant items,
and repairing discrepancies if necessary. Since we issued AD 2012-17-
13, we have determined that all chord segments made of 7079 aluminum
must be replaced with new, improved chord segments made of 7075
aluminum. This proposed AD would add a requirement to replace all chord
segments made of 7079 aluminum with new, improved chord segments made
of 7075 aluminum. We are proposing this AD to detect and correct stress
corrosion and potential early fatigue cracking in the horizontal
stabilizer, which could result in reduced structural integrity of the
horizontal stabilizer.
DATES: We must receive comments on this proposed AD by September 14,
2015.
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.
[[Page 45454]]
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; 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-2015-
2965; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2965;
Directorate Identifier 2014-NM-227-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On August 24, 2012, we issued AD 2012-17-13, Amendment 39-17176 (77
FR 55681, September 11, 2012), for certain The Boeing Company Model 707
airplanes, and Model 720 and 720B series airplanes. For certain
airplanes, AD 2012-17-13 required using redefined flight cycle counts,
determining the type of material of the horizontal stabilizer, rear
spar, and upper and lower chords on the inboard and outboard ends of
the rear spar; repetitively inspecting for cracking of the horizontal
stabilizer components; and repairing or replacing the chord, or
modifying chord segments made from 7079 aluminum, if necessary. For all
airplanes, AD 2012-17-13 required inspecting certain structurally
significant items, and repairing discrepancies if necessary. AD 2012-
17-13 resulted from reports of stress corrosion cracking in the chord
segments made from 7079 aluminum in the horizontal stabilizer rear
spar, and potential early fatigue cracking in the chord segments made
from 7075 aluminum. We issued AD 2012-17-13 to detect and correct
stress corrosion and potential early fatigue cracking in the horizontal
stabilizer, which could compromise the structural integrity of the
stabilizer.
Actions Since AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September
11, 2012), Was Issued
The preamble to AD 2012-17-13, Amendment 39-17176 (77 FR 55681,
September 11, 2012), explained that we considered the requirements
``interim action'' and were considering further rulemaking. We now have
determined that it is necessary to initiate further rulemaking to
continue to require the repetitive inspections required by AD 2012-17-
13, and to add a requirement for replacement of all chord segments made
of 7079 aluminum with new chord segments made of 7075 aluminum. This
proposed AD follows from that determination.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 707 Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014. The service information describes procedures
for incorporating a new cycle counting procedure, determining the
material for the horizontal stabilizer rear spar chord segment,
inspecting for stress corrosion cracking and fatigue cracking, repair,
and replacing all chord segments made of 7079 aluminum with new,
improved chord segments made of 7075 aluminum. This service information
is reasonably available because the interested parties have access to
it through their normal course of business or by the means identified
in the ADDRESSES section of this NPRM.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of these same type
designs.
Proposed AD Requirements
This proposed AD would retain all requirements of AD 2012-17-13,
Amendment 39-17176 (77 FR 55681, September 11, 2012). This proposed AD
would also add a requirement to replace all chord segments made of 7079
aluminum with new chord segments made of 7075 aluminum. This
replacement would not terminate the repetitive inspections required by
AD 2012-17-13.
Costs of Compliance
We estimate that this proposed AD affects 10 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Table--Estimated costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Work hours Parts product Fleet cost
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD Up to 32 work-hours X $0.............. Up to $2,720 Up to $27,200 per
2012-17-13, Amendment 39- $85 per hour = up to per inspection inspection cycle
17176 (77 FR 55681, $2,720 per cycle.
September 11, 2012). inspection cycle.
[[Page 45455]]
Replacement [new action]..... 500 work-hours X $85 Up to $228,000 Up to Up to $23,225,000 \2\
per work-hour = per chord. $2,322,500 (up
$42,500. to 10 chords
per airplane)
\1\.
----------------------------------------------------------------------------------------------------------------
\1\ The parts for the modification could cost up to $2.28 million per airplane, depending on whether only one
operator is ordering the parts or multiple operators. The parts cost will go down if multiple operators order
parts at the same time.
\2\ The number of chords which must be replaced on each specific airplane varies.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2015-2965; Directorate Identifier
2014-NM-227-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by September 14,
2015.
(b) Affected ADs
This AD replaces AD 2012-17-13, Amendment 39-17176 (77 FR 55681,
September 11, 2012).
(c) Applicability
This AD applies to The Boeing Company airplanes, certificated in
any category; identified in paragraphs (c)(1) and (c)(2) of this AD.
(1) Model 707 airplanes identified in Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated October 10, 2014.
(2) Model 720 and 720B series airplanes identified in Boeing 707
Alert Service Bulletin A3516, dated April 4, 2008.
(d) Subject
Air Transport Association (ATA) of America Code 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a determination that all chord segments
made of 7079 aluminum must be replaced with new, improved chord
segments made of 7075 aluminum. We are issuing this AD to detect and
correct stress corrosion and potential early fatigue cracking in the
horizontal stabilizer, which could result in reduced structural
integrity of the horizontal stabilizer.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Flight Cycle Counting Procedure, With Revised Service
Information
This paragraph restates the requirements of paragraph (g) of AD
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. Flight cycles, as used in this AD,
must be counted as defined in the service information identified in
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
(1) Boeing 707 Alert Service Bulletin A3515, dated December 19,
2007 (for Model airplanes).
(2) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated
October 10, 2014 (for Model airplanes).
(3) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008
(for Model airplanes, and Model 720 and 720B series airplanes).
(h) Retained Determination of Material of the Components of the
Horizontal Stabilizer, With Revised Service Information
This paragraph restates the actions required by paragraph (h) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. For airplanes identified in Boeing
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing
707 Alert Service Bulletin A3515, Revision 1, dated October 10,
2014: At the earlier of the times specified in paragraphs (h)(1) and
(h)(2) of this AD, determine the type of material of the horizontal
stabilizer, rear spar, upper chords, and lower chords on the inboard
and outboard ends of the rear spar, in accordance with Part 2 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014.
(1) Within 180 days after October 16, 2012 (the effective date
of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11,
2012)).
(2) Before further flight after any horizontal stabilizer is
replaced after October 16, 2012.
(i) Retained Repetitive Inspections of 7075 Aluminum Components, With
Revised Service Information
This paragraph restates the actions required by paragraph (i) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service
[[Page 45456]]
information. For airplanes with horizontal stabilizer components
made from 7075 aluminum, as determined during the inspection
required by paragraph (h) of this AD: Within 180 days after October
16, 2012 (the effective date of AD 2012-17-13), and before further
flight after any replacement of the horizontal stabilizer, do a
special detailed inspection for cracking of the upper chord on the
inboard end of the rear spar on both the left and right side
horizontal stabilizers, from stabilizer station -13.179 to 92.55, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing
707 Alert Service Bulletin A3515, Revision 1, dated October 10,
2014. Repeat the inspections thereafter at intervals not to exceed
500 flight cycles, and before further flight after any replacement
of the horizontal stabilizer, except as provided by paragraph (j) of
this AD. If any cracking is found, before further flight, either
repair the cracking in accordance with Part 3 of the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3515, dated
December 19, 2007, or Boeing 707 Alert Service Bulletin A3515,
Revision 1, dated October 10, 2014, except as required by paragraph
(n) of this AD; or replace the chord with a new chord, in accordance
with Part 6 of the Accomplishment Instructions of Boeing 707 Alert
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated October 10, 2014.
(j) Retained Repetitive Inspections on Airplanes With Replaced Chord,
With Revised Service Information
This paragraph restates the actions required by paragraph (j) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. For airplanes on which the chord
is replaced with a new chord in accordance with Part 6 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014: Within 4,000 flight
cycles after the chord replacement, do the inspections required by
paragraph (i) of this AD, and repeat the inspections thereafter at
the times specified in paragraph (i) of this AD.
(k) Retained Repetitive Inspections of 7079 Aluminum Components, With
Revised Service Information
This paragraph restates the actions required by paragraph (k) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. For airplanes with horizontal
stabilizers that have components of the chords of the rear spar made
from 7079 aluminum, as determined during the inspection required by
paragraph (h) of this AD: Within 180 days after October 16, 2012
(the effective date of AD 2012-17-13), do the actions required by
paragraphs (k)(1), (k)(2), and (k)(3) of this AD, and repeat those
actions at the applicable intervals specified in paragraphs (k)(1),
(k)(2), and (k)(3) of this AD.
(1) Do a special detailed inspection for cracking of the upper
chord of the inboard side of the rear spar of both the -left and
right-side horizontal stabilizers from stabilizer station -13.179 to
92.55, in accordance with Part 3 of the Accomplishment Instructions
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007,
or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated
October 10, 2014. Repeat the inspection thereafter at intervals not
to exceed 250 flight cycles or 180 days, whichever occurs first. If
any cracking is found during any inspection required by this
paragraph, before further flight, either repair the cracking, in
accordance with Part 3 of the Accomplishment Instructions of Boeing
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing
707 Alert Service Bulletin A3515, Revision 1, dated October 10,
2014, except as required by paragraph (n) of this AD; or replace the
chord with a new chord, in accordance with Part 6 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014.
(2) Do a high frequency eddy current inspection for cracking of
the web flanges of the upper and lower chords of the rear spar in
the left and right side horizontal stabilizers from stabilizer
stations 92.55 to 272.55, in accordance with Part 4 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014. Repeat the inspection
thereafter at intervals not to exceed 1,000 flight cycles or 180
days, whichever occurs first. If any cracking is found during any
inspection required by this paragraph, before further flight, do the
actions specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
(i) Determine whether the cracking meets the limits specified in
Part 4 of the Accomplishment Instructions of Boeing 707 Alert
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated October 10, 2014, and
whether a previous repair has been done; determine if all 7079 upper
and lower chord segments installed on the horizontal stabilizer have
had the Part II, Group 1, Preventative Modification specified in
Boeing Service Bulletin 3356 done; and do all applicable repairs and
modifications, in accordance with the Accomplishment Instructions of
Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or
Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October
10, 2014. Do the actions required by this paragraph in accordance
with Part 4 of the Accomplishment Instructions of Boeing 707 Alert
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated October 10, 2014, except
as required by paragraph (n) of this AD. Do all applicable repairs
and modifications before further flight.
(ii) Replace the chord with a new chord, in accordance with Part
6 of the Accomplishment Instructions of Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated October 10, 2014.
(3) Do low frequency eddy current (LFEC) inspections for
cracking of the forward skin flanges of the upper and lower chords
of the rear spar in the left and right side horizontal stabilizers
from stabilizer stations -13.179 to 272.55 (for lower chords) and
92.55 to 272.55 (for upper chords), in accordance with Part 5 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014. Repeat the inspections
thereafter at intervals not to exceed 1,000 flight cycles or 180
days, whichever occurs first. If any cracking is found during any
inspection required by this paragraph, before further flight, do the
actions specified in either paragraph (k)(3)(i) or paragraph
(k)(3)(ii) of this AD.
(i) Repair any cracking, determine whether all 7079 upper and
lower chord segments installed on the horizontal stabilizer have had
the Part II--Preventative Modification specified in Boeing Service
Bulletin 3381 done, and do all applicable modifications, in
accordance with the Accomplishment Instructions of Boeing 707 Alert
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert
Service Bulletin A3515, Revision 1, dated October 10, 2014. Do the
actions required by this paragraph in accordance with Part 5 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014, except as required by
paragraph (n) of this AD. Do all applicable modifications before
further flight.
(ii) Replace the chord with a new chord, in accordance with Part
6 of the Accomplishment Instructions of Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007; or Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated October 10, 2014.
(l) Retained Modification/Chord Replacement, With Revised Service
Information
This paragraph restates the actions required by paragraph (l) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. For airplanes identified in Boeing
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing
707 Alert Service Bulletin A3515, Revision 1, dated October 10,
2014, with horizontal stabilizers that have rear spar chord
components made from 7079 aluminum and have not had embodied the
modification of Part II of Boeing Service Bulletin 3381, dated July
25, 1980, or Boeing Service Bulletin 3381, Revision 1, dated July
31, 1981: Before further flight after determining the type of
material in accordance with paragraph (h) of this AD, modify all
7079 chord segments installed on the horizontal stabilizer, in
[[Page 45457]]
accordance with Part 5 of the Accomplishment Instructions of Boeing
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing
707 Alert Service Bulletin A3515, Revision 1, dated October 10,
2014; or replace the chord, in accordance with Part 6 of the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014.
(m) Retained Supplemental Structural Inspection Document Inspections
This paragraph restates the actions required by paragraph (m) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012).
For all airplanes: Within 180 days or 1,000 flight cycles after
October 16, 2012 (the effective date of AD 2012-17-13), whichever
occurs first, do the inspections of the applicable structurally
significant items specified in and in accordance with the
Accomplishment Instructions of Boeing 707 Alert Service Bulletin
A3516, dated April 4, 2008. If any cracking is found, before further
flight, repair in accordance with the procedures specified in
paragraph (r) of this AD. The inspections required by AD 85-12-01
R1, Amendment 39-5439 (51 FR 36002, October 8, 1986), are still
required, except, as of October 16, 2012 (the effective date of AD
2012-17-13), the flight-cycle interval for the repetitive
inspections specified in paragraph 1.E., ``Compliance,'' of Boeing
707 Alert Service Bulletin A3516, dated April 4, 2008, must be
counted in accordance with the requirements of paragraph (g) of this
AD.
(n) Retained Exception to Certain Service Information: Contacting FAA
for Crack Repair
This paragraph restates the actions required by paragraph (n) of
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. If any cracking is found during
any inspection required by this AD, and Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated October 10, 2014, specifies to
contact Boeing for appropriate action: Before further flight, repair
the cracking using a method approved in accordance with the
procedures specified in paragraph (r) of this AD.
(o) Retained Exception to Certain Service Information: Nondestructive
Test Compliance Procedures
This paragraph restates the requirements of paragraph (o) of AD
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012),
with revised service information. Where Boeing 707 Alert Service
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated October 10, 2014, specifies that
operators ``refer to'' nondestructive test (NDT) procedures, the
procedures must be done in accordance with the service information
identified in paragraphs (o)(1), (o)(2), and (o)(3) of this AD, as
applicable.
(1) Figure 20, ``Electrical Conductivity Measurement for
Aluminum,'' of Subject 51-00-00, ``Structures-General,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual,
Document D6-48023, Revision 118, dated July 15, 2011.
(2) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6--Eddy
Current, of the Boeing 707/720 Nondestructive Test Manual, Document
D6-48023, Revision 118, dated July 15, 2011.
(3) Subject 51-01-00, ``Orientation and Preparation for
Testing'' of Part 1--General, of the Boeing 707/720 Nondestructive
Test Manual, Document D6-48023, Revision 118, dated July 15, 2011.
(p) Retained Parts Installation Prohibition
As of October 16, 2012 (the effective date of AD 2012-17-13,
Amendment 39-17176 (77 FR 55681, September 11, 2012)), no person may
install any horizontal stabilizer assembly with any chord segment
having a part number other than that identified in paragraph 2.C.2.
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007,
or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated
October 10, 2014, on any airplane.
(q) New Replacement of 7079 Aluminum Components
Within 48 months after the effective date of this AD: Replace
all 7079 aluminum chord segments of the upper and lower chords
installed on the horizontal stabilizer with 7075 aluminum chord
segments, in accordance with Part 6 of the Accomplishment
Instructions of Boeing 707 Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014. Within 4,000 flight cycles after
accomplishing the replacements required by this paragraph, repeat
the inspection required by paragraph (j) of this AD; and repeat the
inspection thereafter at intervals not to exceed 500 flight cycles,
and before further flight after any replacement of the horizontal
stabilizer.
(r) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles 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 (s)(1) of this AD.
Information may be emailed to: 9-ANM-LAACO-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, Los Angeles ACO, to
make those findings. For a repair method to be approved, the repair
must meet the certification basis of the airplane, and the approval
must specifically refer to this AD.
(4) AMOCs approved for AD 2012-17-13, Amendment 39-17176 (77 FR
55681, September 11, 2012), are approved as AMOCs for the
corresponding provisions of this AD.
(s) Related Information
(1) For more information about this AD, contact Chandra Ramdoss,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles
Aircraft Certification Office (ACO), 3960 Paramount Boulevard,
Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210;
email: chandraduth.ramdoss@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001;
telephone 206-544-5000, extension 2; fax 206-766-5683; 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.
Issued in Renton, Washington, on July 16, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-18559 Filed 7-29-15; 8:45 am]
BILLING CODE 4910-13-P
