Document ID: FAA-2015-2965-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2015-07-30T04:00Z

[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: chandraduth.ramdoss@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2965; 
Directorate Identifier 2014-NM-227-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to 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
----------------------------------------------------------------------------------------------------------------
                                                                            Cost per
            Action                   Work hours             Parts           product             Fleet cost
----------------------------------------------------------------------------------------------------------------
Retained inspections from AD   Up to 32 work-hours X  $0..............  Up to $2,720     Up to $27,200 per
 2012-17-13, Amendment 39-      $85 per hour = up to                     per inspection   inspection cycle
 17176 (77 FR 55681,            $2,720 per                               cycle.
 September 11, 2012).           inspection cycle.

[[Page 45455]]

 
Replacement [new action].....  500 work-hours X $85   Up to $228,000    Up to            Up to $23,225,000 \2\
                                per work-hour =        per chord.        $2,322,500 (up
                                $42,500.                                 to 10 chords
                                                                         per airplane)
                                                                         \1\.
----------------------------------------------------------------------------------------------------------------
\1\ The parts for the modification could cost up to $2.28 million per airplane, depending on whether only one
  operator is ordering the parts or multiple operators. The parts cost will go down if multiple operators order
  parts at the same time.
\2\ The number of chords which must be replaced on each specific airplane varies.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), and 
adding the following new AD:

The Boeing Company: Docket No. FAA-2015-2965; Directorate Identifier 
2014-NM-227-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by September 14, 
2015.

(b) Affected ADs

    This AD replaces AD 2012-17-13, Amendment 39-17176 (77 FR 55681, 
September 11, 2012).

(c) Applicability

    This AD applies to The Boeing Company airplanes, certificated in 
any category; identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model 707 airplanes identified in Boeing 707 Alert Service 
Bulletin A3515, Revision 1, dated October 10, 2014.
    (2) Model 720 and 720B series airplanes identified in Boeing 707 
Alert Service Bulletin A3516, dated April 4, 2008.

(d) Subject

    Air Transport Association (ATA) of America Code 55, Stabilizers.

(e) Unsafe Condition

    This AD was prompted by a determination that all chord segments 
made of 7079 aluminum must be replaced with new, improved chord 
segments made of 7075 aluminum. We are issuing this AD to detect and 
correct stress corrosion and potential early fatigue cracking in the 
horizontal stabilizer, which could result in reduced structural 
integrity of the horizontal stabilizer.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Flight Cycle Counting Procedure, With Revised Service 
Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. Flight cycles, as used in this AD, 
must be counted as defined in the service information identified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD.
    (1) Boeing 707 Alert Service Bulletin A3515, dated December 19, 
2007 (for Model airplanes).
    (2) Boeing 707 Alert Service Bulletin A3515, Revision 1, dated 
October 10, 2014 (for Model airplanes).
    (3) Boeing 707 Alert Service Bulletin A3516, dated April 4, 2008 
(for Model airplanes, and Model 720 and 720B series airplanes).

(h) Retained Determination of Material of the Components of the 
Horizontal Stabilizer, With Revised Service Information

    This paragraph restates the actions required by paragraph (h) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. For airplanes identified in Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 
707 Alert Service Bulletin A3515, Revision 1, dated October 10, 
2014: At the earlier of the times specified in paragraphs (h)(1) and 
(h)(2) of this AD, determine the type of material of the horizontal 
stabilizer, rear spar, upper chords, and lower chords on the inboard 
and outboard ends of the rear spar, in accordance with Part 2 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014.
    (1) Within 180 days after October 16, 2012 (the effective date 
of AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 
2012)).
    (2) Before further flight after any horizontal stabilizer is 
replaced after October 16, 2012.

(i) Retained Repetitive Inspections of 7075 Aluminum Components, With 
Revised Service Information

    This paragraph restates the actions required by paragraph (i) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service

[[Page 45456]]

information. For airplanes with horizontal stabilizer components 
made from 7075 aluminum, as determined during the inspection 
required by paragraph (h) of this AD: Within 180 days after October 
16, 2012 (the effective date of AD 2012-17-13), and before further 
flight after any replacement of the horizontal stabilizer, do a 
special detailed inspection for cracking of the upper chord on the 
inboard end of the rear spar on both the left and right side 
horizontal stabilizers, from stabilizer station -13.179 to 92.55, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 
707 Alert Service Bulletin A3515, Revision 1, dated October 10, 
2014. Repeat the inspections thereafter at intervals not to exceed 
500 flight cycles, and before further flight after any replacement 
of the horizontal stabilizer, except as provided by paragraph (j) of 
this AD. If any cracking is found, before further flight, either 
repair the cracking in accordance with Part 3 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, dated 
December 19, 2007, or Boeing 707 Alert Service Bulletin A3515, 
Revision 1, dated October 10, 2014, except as required by paragraph 
(n) of this AD; or replace the chord with a new chord, in accordance 
with Part 6 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert 
Service Bulletin A3515, Revision 1, dated October 10, 2014.

(j) Retained Repetitive Inspections on Airplanes With Replaced Chord, 
With Revised Service Information

    This paragraph restates the actions required by paragraph (j) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. For airplanes on which the chord 
is replaced with a new chord in accordance with Part 6 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014: Within 4,000 flight 
cycles after the chord replacement, do the inspections required by 
paragraph (i) of this AD, and repeat the inspections thereafter at 
the times specified in paragraph (i) of this AD.

(k) Retained Repetitive Inspections of 7079 Aluminum Components, With 
Revised Service Information

    This paragraph restates the actions required by paragraph (k) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. For airplanes with horizontal 
stabilizers that have components of the chords of the rear spar made 
from 7079 aluminum, as determined during the inspection required by 
paragraph (h) of this AD: Within 180 days after October 16, 2012 
(the effective date of AD 2012-17-13), do the actions required by 
paragraphs (k)(1), (k)(2), and (k)(3) of this AD, and repeat those 
actions at the applicable intervals specified in paragraphs (k)(1), 
(k)(2), and (k)(3) of this AD.
    (1) Do a special detailed inspection for cracking of the upper 
chord of the inboard side of the rear spar of both the -left and 
right-side horizontal stabilizers from stabilizer station -13.179 to 
92.55, in accordance with Part 3 of the Accomplishment Instructions 
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, 
or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated 
October 10, 2014. Repeat the inspection thereafter at intervals not 
to exceed 250 flight cycles or 180 days, whichever occurs first. If 
any cracking is found during any inspection required by this 
paragraph, before further flight, either repair the cracking, in 
accordance with Part 3 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 
707 Alert Service Bulletin A3515, Revision 1, dated October 10, 
2014, except as required by paragraph (n) of this AD; or replace the 
chord with a new chord, in accordance with Part 6 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014.
    (2) Do a high frequency eddy current inspection for cracking of 
the web flanges of the upper and lower chords of the rear spar in 
the left and right side horizontal stabilizers from stabilizer 
stations 92.55 to 272.55, in accordance with Part 4 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014. Repeat the inspection 
thereafter at intervals not to exceed 1,000 flight cycles or 180 
days, whichever occurs first. If any cracking is found during any 
inspection required by this paragraph, before further flight, do the 
actions specified in paragraph (k)(2)(i) or (k)(2)(ii) of this AD.
    (i) Determine whether the cracking meets the limits specified in 
Part 4 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert 
Service Bulletin A3515, Revision 1, dated October 10, 2014, and 
whether a previous repair has been done; determine if all 7079 upper 
and lower chord segments installed on the horizontal stabilizer have 
had the Part II, Group 1, Preventative Modification specified in 
Boeing Service Bulletin 3356 done; and do all applicable repairs and 
modifications, in accordance with the Accomplishment Instructions of 
Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, or 
Boeing 707 Alert Service Bulletin A3515, Revision 1, dated October 
10, 2014. Do the actions required by this paragraph in accordance 
with Part 4 of the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert 
Service Bulletin A3515, Revision 1, dated October 10, 2014, except 
as required by paragraph (n) of this AD. Do all applicable repairs 
and modifications before further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service 
Bulletin A3515, Revision 1, dated October 10, 2014.
    (3) Do low frequency eddy current (LFEC) inspections for 
cracking of the forward skin flanges of the upper and lower chords 
of the rear spar in the left and right side horizontal stabilizers 
from stabilizer stations -13.179 to 272.55 (for lower chords) and 
92.55 to 272.55 (for upper chords), in accordance with Part 5 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014. Repeat the inspections 
thereafter at intervals not to exceed 1,000 flight cycles or 180 
days, whichever occurs first. If any cracking is found during any 
inspection required by this paragraph, before further flight, do the 
actions specified in either paragraph (k)(3)(i) or paragraph 
(k)(3)(ii) of this AD.
    (i) Repair any cracking, determine whether all 7079 upper and 
lower chord segments installed on the horizontal stabilizer have had 
the Part II--Preventative Modification specified in Boeing Service 
Bulletin 3381 done, and do all applicable modifications, in 
accordance with the Accomplishment Instructions of Boeing 707 Alert 
Service Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert 
Service Bulletin A3515, Revision 1, dated October 10, 2014. Do the 
actions required by this paragraph in accordance with Part 5 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014, except as required by 
paragraph (n) of this AD. Do all applicable modifications before 
further flight.
    (ii) Replace the chord with a new chord, in accordance with Part 
6 of the Accomplishment Instructions of Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007; or Boeing 707 Alert Service 
Bulletin A3515, Revision 1, dated October 10, 2014.

(l) Retained Modification/Chord Replacement, With Revised Service 
Information

    This paragraph restates the actions required by paragraph (l) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. For airplanes identified in Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 
707 Alert Service Bulletin A3515, Revision 1, dated October 10, 
2014, with horizontal stabilizers that have rear spar chord 
components made from 7079 aluminum and have not had embodied the 
modification of Part II of Boeing Service Bulletin 3381, dated July 
25, 1980, or Boeing Service Bulletin 3381, Revision 1, dated July 
31, 1981: Before further flight after determining the type of 
material in accordance with paragraph (h) of this AD, modify all 
7079 chord segments installed on the horizontal stabilizer, in

[[Page 45457]]

accordance with Part 5 of the Accomplishment Instructions of Boeing 
707 Alert Service Bulletin A3515, dated December 19, 2007, or Boeing 
707 Alert Service Bulletin A3515, Revision 1, dated October 10, 
2014; or replace the chord, in accordance with Part 6 of the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3515, dated December 19, 2007, or Boeing 707 Alert Service Bulletin 
A3515, Revision 1, dated October 10, 2014.

(m) Retained Supplemental Structural Inspection Document Inspections

    This paragraph restates the actions required by paragraph (m) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012). 
For all airplanes: Within 180 days or 1,000 flight cycles after 
October 16, 2012 (the effective date of AD 2012-17-13), whichever 
occurs first, do the inspections of the applicable structurally 
significant items specified in and in accordance with the 
Accomplishment Instructions of Boeing 707 Alert Service Bulletin 
A3516, dated April 4, 2008. If any cracking is found, before further 
flight, repair in accordance with the procedures specified in 
paragraph (r) of this AD. The inspections required by AD 85-12-01 
R1, Amendment 39-5439 (51 FR 36002, October 8, 1986), are still 
required, except, as of October 16, 2012 (the effective date of AD 
2012-17-13), the flight-cycle interval for the repetitive 
inspections specified in paragraph 1.E., ``Compliance,'' of Boeing 
707 Alert Service Bulletin A3516, dated April 4, 2008, must be 
counted in accordance with the requirements of paragraph (g) of this 
AD.

(n) Retained Exception to Certain Service Information: Contacting FAA 
for Crack Repair

    This paragraph restates the actions required by paragraph (n) of 
AD 2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. If any cracking is found during 
any inspection required by this AD, and Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service 
Bulletin A3515, Revision 1, dated October 10, 2014, specifies to 
contact Boeing for appropriate action: Before further flight, repair 
the cracking using a method approved in accordance with the 
procedures specified in paragraph (r) of this AD.

(o) Retained Exception to Certain Service Information: Nondestructive 
Test Compliance Procedures

    This paragraph restates the requirements of paragraph (o) of AD 
2012-17-13, Amendment 39-17176 (77 FR 55681, September 11, 2012), 
with revised service information. Where Boeing 707 Alert Service 
Bulletin A3515, dated December 19, 2007, or Boeing 707 Alert Service 
Bulletin A3515, Revision 1, dated October 10, 2014, specifies that 
operators ``refer to'' nondestructive test (NDT) procedures, the 
procedures must be done in accordance with the service information 
identified in paragraphs (o)(1), (o)(2), and (o)(3) of this AD, as 
applicable.
    (1) Figure 20, ``Electrical Conductivity Measurement for 
Aluminum,'' of Subject 51-00-00, ``Structures-General,'' of Part 6--
Eddy Current, of the Boeing 707/720 Nondestructive Test Manual, 
Document D6-48023, Revision 118, dated July 15, 2011.
    (2) Subject 55-10-07, ``Horizontal Stabilizer,'' of Part 6--Eddy 
Current, of the Boeing 707/720 Nondestructive Test Manual, Document 
D6-48023, Revision 118, dated July 15, 2011.
    (3) Subject 51-01-00, ``Orientation and Preparation for 
Testing'' of Part 1--General, of the Boeing 707/720 Nondestructive 
Test Manual, Document D6-48023, Revision 118, dated July 15, 2011.

(p) Retained Parts Installation Prohibition

    As of October 16, 2012 (the effective date of AD 2012-17-13, 
Amendment 39-17176 (77 FR 55681, September 11, 2012)), no person may 
install any horizontal stabilizer assembly with any chord segment 
having a part number other than that identified in paragraph 2.C.2. 
of Boeing 707 Alert Service Bulletin A3515, dated December 19, 2007, 
or Boeing 707 Alert Service Bulletin A3515, Revision 1, dated 
October 10, 2014, on any airplane.

(q) New Replacement of 7079 Aluminum Components

    Within 48 months after the effective date of this AD: Replace 
all 7079 aluminum chord segments of the upper and lower chords 
installed on the horizontal stabilizer with 7075 aluminum chord 
segments, in accordance with Part 6 of the Accomplishment 
Instructions of Boeing 707 Alert Service Bulletin A3515, Revision 1, 
dated October 10, 2014. Within 4,000 flight cycles after 
accomplishing the replacements required by this paragraph, repeat 
the inspection required by paragraph (j) of this AD; and repeat the 
inspection thereafter at intervals not to exceed 500 flight cycles, 
and before further flight after any replacement of the horizontal 
stabilizer.

(r) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested using the procedures found in 14 CFR 39.19. In accordance 
with 14 CFR 39.19, send your request to your principal inspector or 
local Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in paragraph (s)(1) of this AD. 
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Los Angeles ACO, to 
make those findings. For a repair method to be approved, the repair 
must meet the certification basis of the airplane, and the approval 
must specifically refer to this AD.
    (4) AMOCs approved for AD 2012-17-13, Amendment 39-17176 (77 FR 
55681, September 11, 2012), are approved as AMOCs for the 
corresponding provisions of this AD.

(s) Related Information

    (1) For more information about this AD, contact Chandra Ramdoss, 
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles 
Aircraft Certification Office (ACO), 3960 Paramount Boulevard, 
Lakewood, CA 90712-4137; phone: 562-627-5239; fax: 562-627-5210; 
email: chandraduth.ramdoss@faa.gov.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; 
telephone 206-544-5000, extension 2; fax 206-766-5683; Internet 
https://www.myboeingfleet.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on July 16, 2015.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2015-18559 Filed 7-29-15; 8:45 am]
 BILLING CODE 4910-13-P