AD 2016-08-11

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-08539]


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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; 
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.

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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 <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and 
locating Docket No. FAA-2015-2965.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#2c4f444d42485e4d48595844025e4d4148435f5f6c4a4d4d024b435a"><span class="__cf_email__" data-cfemail="c8aba0a9a6acbaa9acbdbca0e6baa9a5aca7bbbb88aea9a9e6afa7be">[email&#160;protected]</span></a>.

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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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: <a href="/cdn-cgi/l/email-protection#8ab3a7cbc4c7a7c6cbcbc9c5a7cbc7c5c9a7d8effbffeff9fef9caecebeba4ede5fc"><span class="__cf_email__" data-cfemail="8bb2a6cac5c6a6c7cacac8c4a6cac6c4c8a6d9eefafeeef8fff8cbedeaeaa5ece4fd">[email&#160;protected]</span></a>.
    (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: <a href="/cdn-cgi/l/email-protection#cfaca7aea1abbdaeabbabba7e1bdaea2aba0bcbc8fa9aeaee1a8a0b9"><span class="__cf_email__" data-cfemail="81e2e9e0efe5f3e0e5f4f5e9aff3e0ece5eef2f2c1e7e0e0afe6eef7">[email&#160;protected]</span></a>.

(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 
<a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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