[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]
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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).
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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 http://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 http://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: [email protected].
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 http://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
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Cost per
Action Work hours Parts product Fleet cost
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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\.
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\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: [email protected].
(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: [email protected].
(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]
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