Airworthiness Directives; The Boeing Company Airplanes, 23586-23591 [2016-08539]
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Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations
assembly part number 2447M10G01 or
2447M10G02: Before October 1, 2016, do the
actions specified by paragraph (j)(1) or (j)(2)
of this AD.
(1) Rework at least one engine in
accordance with paragraph 3.B. or 3.C. of the
Accomplishment Instructions of GE GEnx–1B
Service Bulletin 72–0309 R00, dated March
11, 2016; or paragraph 3.B. or 3.C. of the
Accomplishment Instructions of GE GEnx–1B
Service Bulletin 72–0314 R00, dated April 1,
2016. Although GE GEnx Service Bulletins
GEnx–1B 72–0314 R00, dated April 1, 2016;
and GEnx–1B 72–0309 R00, dated March 11,
2016; specify submitting certain tip clearance
measurements to GE, no report is required by
this AD.
(2) Remove at least one engine and replace
with an engine that is eligible for installation
that is not identified in the introductory text
to paragraph (j) of this AD.
(k) 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 (l) of this AD. Information may be
emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
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(l) Related Information
For more information about this AD,
contact Sue Lucier, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6438; fax: 425–
917–6590; email: Suzanne.Lucier@faa.gov.
(m) 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 May 9, 2016.
(i) GE GEnx–1B Service Bulletin 72–0314
R00, dated April 1, 2016.
(ii) Reserved.
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(4) The following service information was
approved for IBR on March 18, 2016 (81 FR
14704, March 18, 2016).
(i) GE GEnx–1B Service Bulletin 72–0309
R00, dated March 11, 2016.
(ii) Reserved.
(5) For service information identified in
this AD, contact General Electric Company,
GE Aviation, Room 285, 1 Neumann Way,
Cincinnati, OH 45215; phone: 513–552–3272;
email: aviation.fleetsupport@ge.com.
(6) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Burlington, Massachusetts, on
April 7, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
Issued in Renton, Washington, on April 12,
2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–09000 Filed 4–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2965; Directorate
Identifier 2014–NM–227–AD; Amendment
39–18487; AD 2016–08–11]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2012–17–
13, which applied 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
SUMMARY:
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airplanes, AD 2012–17–13 required
inspecting certain structurally
significant items, and repairing
discrepancies if necessary. This new AD
adds a requirement to replace all chord
segments made of 7079 aluminum with
new, improved chord segments made of
7075 aluminum. 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.
DATES: This AD is effective May 27,
2016.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of May 27, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of October 16, 2012 (77 FR
55681, September 11, 2012).
ADDRESSES: For service information
identified in this final rule, 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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2965.
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (phone: 800–647–5527) is
Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
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Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations
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:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012) (‘‘AD 2012–17–
13’’). AD 2012–17–13 applied to certain
The Boeing Company Model 707
airplanes, and Model 720 and 720B
series airplanes. The NPRM published
in the Federal Register on July 30, 2015
(80 FR 45453) (‘‘the NPRM’’). The
NPRM 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. The
NPRM proposed to continue to require,
for certain airplanes, 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. The NPRM also proposed to
continue to require, for all airplanes,
inspecting certain structurally
significant items, and repairing
discrepancies if necessary. The NPRM
proposed to add a requirement to
replace all chord segments made of 7079
aluminum 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 compromise the
structural integrity of the stabilizer.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Clarify Certain Language in
Paragraph (i) of the Proposed AD
Boeing asked that we clarify the
description of the affected components
specified in paragraph (i) of the
proposed AD, which is a restatement of
paragraph (i) of AD 2012–17–13. Boeing
stated that the intent of paragraph (i) of
AD 2012–17–13 was to specify the
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inspection requirements for rear spar
upper inboard chord segments made
from 7075 aluminum. Boeing added that
the restatement in paragraph (i) of the
proposed AD specifies, ‘‘For all
airplanes with horizontal stabilizer
components made from 7075 . . .’’ and
noted that this description could apply
to any chord segment, not just the
inboard upper. Boeing asked that the
description be clarified to specify ‘‘any
horizontal stabilizer with a rear spar
upper inboard chord segment made
from 7075 aluminum, as determined
during the inspection required by
paragraph (h) of this AD.’’
We agree to clarify paragraph (i) of
this AD. The inspection required by
paragraph (i) of this AD must be done
on upper chords made from 7075
aluminum that are on the inboard end
of the rear spar, as specified in Boeing
707 Alert Service Bulletin A3515, dated
December 19, 2007; and Boeing 707
Alert Service Bulletin A3515, Revision
1, dated October 10, 2014; which are the
appropriate sources of service
information for accomplishing the
required actions. We have revised
paragraph (i) of this AD to clarify the
inspection requirements. No additional
action is necessary for operators that
have already complied with paragraph
(i) of this AD.
Request To Clarify Certain Language in
Paragraph (j) of the Proposed AD
Boeing also asked that we clarify the
language in the restatement of actions
specified in paragraph (j) of the
proposed AD in order to specify that the
inspections in paragraph (i) of the
proposed AD can only be deferred for
4,000 flight cycles if the upper inboard
chord is replaced with a new chord.
Boeing stated that changing paragraph
(i) of the proposed AD ensures that it is
clear that the inspection can only be
deferred for 4,000 flight cycles if the
upper inboard chord is replaced.
We agree with the commenter for the
reason provided. We have changed
paragraph (j) of this AD to specify ‘‘For
airplanes on which the rear spar upper
inner chord is replaced with a new
chord . . . :’’
Request To Clarify Certain Language in
Paragraph (q) of the Proposed AD
Boeing also asked that we clarify the
language in the new actions specified in
paragraph (q) of the proposed AD.
Boeing stated that paragraph (j) of the
proposed AD states when to resume the
inspections after the chord is replaced.
Boeing added that paragraph (i) of the
proposed AD states the type of
inspection and the repetitive inspection
interval. Therefore, Boeing stated that
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23587
paragraph (q) of the proposed AD
should point to paragraph (i) of the
proposed AD.
We agree to clarify paragraph (q) of
this AD. As noted above, paragraph (j)
of the this AD specifies inspecting the
new chord within 4,000 flight cycles
after the chord replacement, as required
by paragraph (i) of this AD, and
repeating the inspections thereafter at
the times specified in paragraph (i) of
this AD. Therefore, we have included
similar language in paragraph (q) of this
AD.
Request To Clarify Service Information
References
In addition, Boeing asked that we
include 707 in the title for ‘‘Boeing
Service Bulletin 3381,’’ as identified in
paragraphs (k) and (l) of the proposed
AD, to be consistent with all the other
service information references in the
NPRM.
We agree with the commenter for the
reasons provided. We have changed the
service information references in
paragraphs (k)(3)(i) and (l) of this AD to
specify ‘‘Boeing 707 Service Bulletin
3381.’’
Boeing also asked that we change the
semi-colon (located between the service
information references) in paragraph
(k)(3)(ii) of the proposed AD to a
comma, because it breaks up the
sentence in an unintended way.
We do not agree to change the semicolon in paragraph (k)(3)(ii) of this AD.
In ADs, we use a semi-colon to separate
service information references, except in
cases where the semi-colon between
service information might cause
confusion, e.g., a sentence that already
uses semi-colons between text other
than the service information. The semicolon in paragraph (k)(3)(ii) of this AD
does not change the intent of that
paragraph. We have not changed this
AD in this regard.
Conclusion
We reviewed the available data and
determined that air safety and the
public interest require adopting this AD
with the changes described previously,
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing 707 Alert Service
Bulletin A3515, Revision 1, dated
October 10, 2014. The service
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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.
Costs of Compliance
We estimate that this AD affects 10
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
TABLE—ESTIMATED COSTS
Action
Work hours
Parts
Cost per product
Fleet cost
Retained inspections
from AD 2012–17–
13.
Replacement [new action].
Up to 32 work-hours × $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.
500 work-hours × $85 per work-hour =
$42,500 per chord.
Up to $228,000 per
chord.
Up to $2,705,000 (up
to 10 chords per
airplane) 1.
Up to $27,050,000.2
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.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
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on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2012–17–13, Amendment 39–17176 (77
FR 55681, September 11, 2012), and
adding the following new AD:
■
2016–08–11 The Boeing Company:
Amendment 39–18487; Docket No.
FAA–2015–2965; Directorate Identifier
2014–NM–227–AD.
(a) Effective Date
This AD is effective May 27, 2016.
(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.
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(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
707 airplanes).
(2) Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014
(for Model 707 airplanes).
(3) Boeing 707 Alert Service Bulletin
A3516, dated April 4, 2008 (for Model 707
airplanes, and Model 720 and 720B series
airplanes).
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(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 and Affected
Component Description
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
information and affected component
description. For airplanes with any
horizontal stabilizer with a rear spar upper
inboard chord segment 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 and Revised
Language for Affected Airplanes
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 and revised langue for affected
airplanes. For airplanes on which the rear
spar upper inner 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, inspect the new
chord, as 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
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23589
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 707 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 707 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
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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.
asabaliauskas on DSK3SPTVN1PROD with RULES
(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 707 Service Bulletin 3381,
dated July 25, 1980; or Boeing 707 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 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
using a method approved 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
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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
With Revised Service Information
This paragraph restates the parts
installation prohibition required by
paragraph (p) of AD 2012–17–13,
Amendment 39–17176 (77 FR 55681,
September 11, 2012), with revised service
information. 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.
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Fmt 4700
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(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, inspect the new
chord, as required by paragraph (i) of this
AD, and repeat the inspections thereafter at
the times specified in paragraph (i) of this
AD.
(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) 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,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) 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
For more information about this AD,
contact Chandra Ramdoss, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles ACO, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5239; fax: 562–627–5210;
email: chandraduth.ramdoss@faa.gov.
(t) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing 707 Alert Service Bulletin
A3515, Revision 1, dated October 10, 2014.
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(ii) Reserved.
(3) The following service information was
approved for IBR on October 16, 2012 (77 FR
55681, September 11, 2012).
(i) Boeing 707 Alert Service Bulletin
A3515, dated December 19, 2007.
(ii) Boeing 707 Alert Service Bulletin
A3516, dated April 4, 2008.
(iii) Subject 51–00–00, ‘‘StructuresGeneral,’’ Figure 20, ‘‘Electrical Conductivity
Measurement for Aluminum,’’ of Part 6—
Eddy Current, of the Boeing 707/720
Nondestructive Test Manual, Document D6–
48023, Revision 118, dated July 15, 2011. The
revision level of this document is identified
on only the manual revision Transmittal
Sheet.
(iv) 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. The revision level of this
document is identified on only the manual
revision Transmittal Sheet.
(v) 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. The revision level of this
document is identified on only the manual
revision Transmittal Sheet.
(4) 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.
(5) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(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/ibrlocations.html.
Issued in Renton, Washington, on April 5,
2016.
Suzanne Masterson,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–08539 Filed 4–21–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2015–5194; Airspace
Docket No. 15–ACE–6]
Establishment of Class E Airspace;
Coldwater, KS
Federal Aviation
Administration (FAA), DOT.
AGENCY:
VerDate Sep<11>2014
16:23 Apr 21, 2016
Jkt 238001
ACTION:
Final rule.
This action establishes Class
E airspace in Coldwater, KS. Controlled
airspace is necessary to accommodate
new Standard Instrument Approach
Procedures (SIAPs) at Comanche County
Airport. The FAA is taking this action
to enhance the safety and management
of Instrument Flight Rule (IFR)
operations at the airport. Additionally,
to this action corrects the spelling of the
airport name to Comanche County
Airport, inadvertently misspelled in the
proposal.
DATES: Effective 0901 UTC, July 21,
2016. The Director of the Federal
Register approves this incorporation by
reference action under title 1, Code of
Federal Regulations, part 51, subject to
the annual revision of FAA Order
7400.9 and publication of conforming
amendments.
ADDRESSES: FAA Order 7400.9Z,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed on line at https://
www.faa.gov/airtraffic/publications/.
For further information, you can contact
the Airspace Policy Group, Federal
Aviation Administration, 800
Independence Avenue SW.,
Washington, DC 20591; telephone: 202–
267–8783. The Order is also available
for inspection 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/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.9, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT:
Rebecca Shelby, Central Service Center,
Operations Support Group, Federal
Aviation Administration, Southwest
Region, 10101 Hillwood Parkway, Fort
Worth, TX 76177; telephone: (817) 222–
5857.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking is
promulgated under the authority
described in Subtitle VII, Part, A,
Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
PO 00000
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Fmt 4700
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23591
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it establishes
controlled airspace at Comanche County
Airport, Coldwater, KS.
History
On February 11, 2016, the FAA
published in the Federal Register a
notice of proposed rulemaking (NPRM)
to establish Class E Airspace in the
Coldwater, KS area. (81 FR 7251) FAA
2015–5194. Interested parties were
invited to participate in this rulemaking
effort by submitting written comments
on the proposal to the FAA. No
comments were received.
Class E airspace designations are
published in paragraph 6005 of FAA
Order 7400.9Z dated August 6, 2015,
and effective September 15, 2015, which
is incorporated by reference in 14 CFR
part 71.1. The Class E airspace
designations listed in this document
will be published subsequently in the
Order.
Availability and Summary of
Documents for Incorporation by
Reference
This document amends FAA Order
7400.9Z, airspace Designations and
Reporting Points, dated August 6, 2015,
and effective September 15, 2015. FAA
Order 7400.9Z is publicly available as
listed in the ADDRESSES section of this
document. FAA Order 7400.9Z lists
Class A, B, C, D, and E airspace areas,
air traffic service routes, and reporting
points.
The Rule
This amendment to Title 14, Code of
Federal Regulations (14 CFR) part 71
establishes Class E airspace extending
upward from 700 feet above the surface
within a 7.5-mile radius of Comanche
County Airport, Coldwater, KS, to
accommodate new standard instrument
approach procedures. Controlled
airspace is needed for the safety and
management of IFR operations at the
airport. Additionally, the airport name
is corrected from Commanche County
Airport to Comanche County Airport.
Class E airspace designations are
published in Paragraph 6005 of FAA
Order 7400.9Z, dated August 6, 2015,
and effective September 15, 2015, which
is incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document will be
published subsequently in the Order.
Regulatory Notices and Analyses
The FAA has determined that this
regulation only involves an established
body of technical regulations for which
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]]>Agencies
[Federal Register Volume 81, Number 78 (Friday, April 22, 2016)]
[Rules and Regulations]
[Pages 23586-23591]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08539]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2965; Directorate Identifier 2014-NM-227-AD;
Amendment 39-18487; AD 2016-08-11]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2012-17-13,
which applied 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. This new AD adds a
requirement to replace all chord segments made of 7079 aluminum with
new, improved chord segments made of 7075 aluminum. 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.
DATES: This AD is effective May 27, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 27,
2016.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of October
16, 2012 (77 FR 55681, September 11, 2012).
ADDRESSES: For service information identified in this final rule,
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. It is also available on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2015-2965.
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 AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.
[[Page 23587]]
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:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2012-17-13, Amendment 39-17176 (77 FR 55681,
September 11, 2012) (``AD 2012-17-13''). AD 2012-17-13 applied to
certain The Boeing Company Model 707 airplanes, and Model 720 and 720B
series airplanes. The NPRM published in the Federal Register on July
30, 2015 (80 FR 45453) (``the NPRM''). The NPRM 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. The
NPRM proposed to continue to require, for certain airplanes, 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. The NPRM also proposed to continue to require,
for all airplanes, inspecting certain structurally significant items,
and repairing discrepancies if necessary. The NPRM proposed to add a
requirement to replace all chord segments made of 7079 aluminum 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 compromise the
structural integrity of the stabilizer.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Clarify Certain Language in Paragraph (i) of the Proposed AD
Boeing asked that we clarify the description of the affected
components specified in paragraph (i) of the proposed AD, which is a
restatement of paragraph (i) of AD 2012-17-13. Boeing stated that the
intent of paragraph (i) of AD 2012-17-13 was to specify the inspection
requirements for rear spar upper inboard chord segments made from 7075
aluminum. Boeing added that the restatement in paragraph (i) of the
proposed AD specifies, ``For all airplanes with horizontal stabilizer
components made from 7075 . . .'' and noted that this description could
apply to any chord segment, not just the inboard upper. Boeing asked
that the description be clarified to specify ``any horizontal
stabilizer with a rear spar upper inboard chord segment made from 7075
aluminum, as determined during the inspection required by paragraph (h)
of this AD.''
We agree to clarify paragraph (i) of this AD. The inspection
required by paragraph (i) of this AD must be done on upper chords made
from 7075 aluminum that are on the inboard end of the rear spar, as
specified in Boeing 707 Alert Service Bulletin A3515, dated December
19, 2007; and Boeing 707 Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014; which are the appropriate sources of service
information for accomplishing the required actions. We have revised
paragraph (i) of this AD to clarify the inspection requirements. No
additional action is necessary for operators that have already complied
with paragraph (i) of this AD.
Request To Clarify Certain Language in Paragraph (j) of the Proposed AD
Boeing also asked that we clarify the language in the restatement
of actions specified in paragraph (j) of the proposed AD in order to
specify that the inspections in paragraph (i) of the proposed AD can
only be deferred for 4,000 flight cycles if the upper inboard chord is
replaced with a new chord. Boeing stated that changing paragraph (i) of
the proposed AD ensures that it is clear that the inspection can only
be deferred for 4,000 flight cycles if the upper inboard chord is
replaced.
We agree with the commenter for the reason provided. We have
changed paragraph (j) of this AD to specify ``For airplanes on which
the rear spar upper inner chord is replaced with a new chord . . . :''
Request To Clarify Certain Language in Paragraph (q) of the Proposed AD
Boeing also asked that we clarify the language in the new actions
specified in paragraph (q) of the proposed AD. Boeing stated that
paragraph (j) of the proposed AD states when to resume the inspections
after the chord is replaced. Boeing added that paragraph (i) of the
proposed AD states the type of inspection and the repetitive inspection
interval. Therefore, Boeing stated that paragraph (q) of the proposed
AD should point to paragraph (i) of the proposed AD.
We agree to clarify paragraph (q) of this AD. As noted above,
paragraph (j) of the this AD specifies inspecting the new chord within
4,000 flight cycles after the chord replacement, as required by
paragraph (i) of this AD, and repeating the inspections thereafter at
the times specified in paragraph (i) of this AD. Therefore, we have
included similar language in paragraph (q) of this AD.
Request To Clarify Service Information References
In addition, Boeing asked that we include 707 in the title for
``Boeing Service Bulletin 3381,'' as identified in paragraphs (k) and
(l) of the proposed AD, to be consistent with all the other service
information references in the NPRM.
We agree with the commenter for the reasons provided. We have
changed the service information references in paragraphs (k)(3)(i) and
(l) of this AD to specify ``Boeing 707 Service Bulletin 3381.''
Boeing also asked that we change the semi-colon (located between
the service information references) in paragraph (k)(3)(ii) of the
proposed AD to a comma, because it breaks up the sentence in an
unintended way.
We do not agree to change the semi-colon in paragraph (k)(3)(ii) of
this AD. In ADs, we use a semi-colon to separate service information
references, except in cases where the semi-colon between service
information might cause confusion, e.g., a sentence that already uses
semi-colons between text other than the service information. The semi-
colon in paragraph (k)(3)(ii) of this AD does not change the intent of
that paragraph. We have not changed this AD in this regard.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting this AD with the changes described
previously, and minor editorial changes. We have determined that these
minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing 707 Alert Service Bulletin A3515, Revision 1,
dated October 10, 2014. The service
[[Page 23588]]
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.
Costs of Compliance
We estimate that this AD affects 10 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Table--Estimated Costs
----------------------------------------------------------------------------------------------------------------
Action Work hours Parts Cost per product Fleet cost
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD Up to 32 work-hours x $0............... Up to $2,720 per Up to $27,200 per
2012-17-13. $85 per hour = up to inspection cycle. inspection
$2,720 per inspection cycle.
cycle.
Replacement [new action]....... 500 work-hours x $85 Up to $228,000 Up to $2,705,000 Up to
per work-hour = per chord. (up to 10 chords $27,050,000.2
$42,500 per chord. 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 AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), and
adding the following new AD:
2016-08-11 The Boeing Company: Amendment 39-18487; Docket No. FAA-
2015-2965; Directorate Identifier 2014-NM-227-AD.
(a) Effective Date
This AD is effective May 27, 2016.
(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 707 airplanes).
(2) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated
October 10, 2014 (for Model 707 airplanes).
(3) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008
(for Model 707 airplanes, and Model 720 and 720B series airplanes).
[[Page 23589]]
(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 and Affected Component Description
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 information and affected component description.
For airplanes with any horizontal stabilizer with a rear spar upper
inboard chord segment 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 and Revised Language for Affected
Airplanes
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 and revised langue for affected
airplanes. For airplanes on which the rear spar upper inner 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, inspect the new chord, as
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 707 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 707
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
[[Page 23590]]
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 707 Service Bulletin 3381, dated
July 25, 1980; or Boeing 707 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
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 using a method approved 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 With Revised Service
Information
This paragraph restates the parts installation prohibition
required by paragraph (p) of AD 2012-17-13, Amendment 39-17176 (77
FR 55681, September 11, 2012), with revised service information. 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, inspect
the new chord, as required by paragraph (i) of this AD, and repeat
the inspections thereafter at the times specified in paragraph (i)
of this AD.
(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) 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, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Los Angeles ACO, to make those findings. To be approved,
the repair method, modification deviation, or alteration deviation
must meet the certification basis of the airplane, and the approval
must specifically refer to this AD.
(4) 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
For more information about this AD, contact Chandra Ramdoss,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5239; fax: 562-627-5210; email: chandraduth.ramdoss@faa.gov.
(t) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated
October 10, 2014.
[[Page 23591]]
(ii) Reserved.
(3) The following service information was approved for IBR on
October 16, 2012 (77 FR 55681, September 11, 2012).
(i) Boeing 707 Alert Service Bulletin A3515, dated December 19,
2007.
(ii) Boeing 707 Alert Service Bulletin A3516, dated April 4,
2008.
(iii) Subject 51-00-00, ``Structures-General,'' Figure 20,
``Electrical Conductivity Measurement for Aluminum,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual,
Document D6-48023, Revision 118, dated July 15, 2011. The revision
level of this document is identified on only the manual revision
Transmittal Sheet.
(iv) 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.
The revision level of this document is identified on only the manual
revision Transmittal Sheet.
(v) 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. The revision level of
this document is identified on only the manual revision Transmittal
Sheet.
(4) 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.
(5) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(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 April 5, 2016.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-08539 Filed 4-21-16; 8:45 am]
BILLING CODE 4910-13-P
