23586 Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 

assembly part number 2447M10G01 or 

2447M10G02: Before October 1, 2016, do the 

actions specified by paragraph (j)(1) or (j)(2) 

of this AD. 

(1) Rework at least one engine in 

accordance with paragraph 3.B. or 3.C. of the 

Accomplishment Instructions of GE GEnx–1B 

Service Bulletin 72–0309 R00, dated March 

11, 2016; or paragraph 3.B. or 3.C. of the 

Accomplishment Instructions of GE GEnx–1B 

Service Bulletin 72–0314 R00, dated April 1, 

2016. Although GE GEnx Service Bulletins 

GEnx–1B 72–0314 R00, dated April 1, 2016; 

and GEnx–1B 72–0309 R00, dated March 11, 

2016; specify submitting certain tip clearance 

measurements to GE, no report is required by 

this AD. 

(2) Remove at least one engine and replace 

with an engine that is eligible for installation 

that is not identified in the introductory text 

to paragraph (j) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(l) Related Information 

For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6438; fax: 425– 

917–6590; email: Suzanne.Lucier@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 9, 2016. 

(i) GE GEnx–1B Service Bulletin 72–0314 

R00, dated April 1, 2016. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on March 18, 2016 (81 FR 

14704, March 18, 2016). 

(i) GE GEnx–1B Service Bulletin 72–0309 

R00, dated March 11, 2016. 

(ii) Reserved. 

(5) For service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: aviation.fleetsupport@ge.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

April 7, 2016. 

Ann C. Mollica, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

Issued in Renton, Washington, on April 12, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09000 Filed 4–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2965; Directorate 

Identifier 2014–NM–227–AD; Amendment 

39–18487; AD 2016–08–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2012–17– 

13, which applied to certain The Boeing 

Company Model 707 airplanes, and 

Model 720 and 720B series airplanes. 

For certain airplanes, AD 2012–17–13 

required using redefined flight cycle 

counts; determining the type of material 

of the horizontal stabilizer, rear spar, 

and upper and lower chords on the 

inboard and outboard ends of the rear 

spar; repetitively inspecting for cracking 

of the horizontal stabilizer components; 

and repairing or replacing the chord, or 

modifying chord segments made of 7079 

aluminum, if necessary. For all 

airplanes, AD 2012–17–13 required 

inspecting certain structurally 

significant items, and repairing 

discrepancies if necessary. This new AD 

adds a requirement to replace all chord 

segments made of 7079 aluminum with 

new, improved chord segments made of 

7075 aluminum. This AD was prompted 

by a determination that all chord 

segments made of 7079 aluminum must 

be replaced with new, improved chord 

segments made of 7075 aluminum. We 

are issuing this AD to detect and correct 

stress corrosion and potential early 

fatigue cracking in the horizontal 

stabilizer, which could result in reduced 

structural integrity of the horizontal 

stabilizer. 

DATES: This AD is effective May 27, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 16, 2012 (77 FR 

55681, September 11, 2012). 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

3855 Lakewood Boulevard, MC D800– 

0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2965. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 


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Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 23587 

FOR FURTHER INFORMATION CONTACT: 

Chandra Ramdoss, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 

562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012) (‘‘AD 2012–17– 

13’’). AD 2012–17–13 applied to certain 

The Boeing Company Model 707 

airplanes, and Model 720 and 720B 

series airplanes. The NPRM published 

in the Federal Register on July 30, 2015 

(80 FR 45453) (‘‘the NPRM’’). The 

NPRM was prompted by a 

determination that all chord segments 

made of 7079 aluminum must be 

replaced with new, improved chord 

segments made of 7075 aluminum. The 

NPRM proposed to continue to require, 

for certain airplanes, using redefined 

flight cycle counts, determining the type 

of material of the horizontal stabilizer, 

rear spar, and upper and lower chords 

on the inboard and outboard ends of the 

rear spar; repetitively inspecting for 

cracking of the horizontal stabilizer 

components; and repairing or replacing 

the chord, or modifying chord segments 

made from 7079 aluminum, if 

necessary. The NPRM also proposed to 

continue to require, for all airplanes, 

inspecting certain structurally 

significant items, and repairing 

discrepancies if necessary. The NPRM 

proposed to add a requirement to 

replace all chord segments made of 7079 

aluminum with new, improved chord 

segments made of 7075 aluminum. We 

are issuing this AD to detect and correct 

stress corrosion and potential early 

fatigue cracking in the horizontal 

stabilizer, which could compromise the 

structural integrity of the stabilizer. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Clarify Certain Language in 

Paragraph (i) of the Proposed AD 

Boeing asked that we clarify the 

description of the affected components 

specified in paragraph (i) of the 

proposed AD, which is a restatement of 

paragraph (i) of AD 2012–17–13. Boeing 

stated that the intent of paragraph (i) of 

AD 2012–17–13 was to specify the 

inspection requirements for rear spar 

upper inboard chord segments made 

from 7075 aluminum. Boeing added that 

the restatement in paragraph (i) of the 

proposed AD specifies, ‘‘For all 

airplanes with horizontal stabilizer 

components made from 7075 . . .’’ and 

noted that this description could apply 

to any chord segment, not just the 

inboard upper. Boeing asked that the 

description be clarified to specify ‘‘any 

horizontal stabilizer with a rear spar 

upper inboard chord segment made 

from 7075 aluminum, as determined 

during the inspection required by 

paragraph (h) of this AD.’’ 

We agree to clarify paragraph (i) of 

this AD. The inspection required by 

paragraph (i) of this AD must be done 

on upper chords made from 7075 

aluminum that are on the inboard end 

of the rear spar, as specified in Boeing 

707 Alert Service Bulletin A3515, dated 

December 19, 2007; and Boeing 707 

Alert Service Bulletin A3515, Revision 

1, dated October 10, 2014; which are the 

appropriate sources of service 

information for accomplishing the 

required actions. We have revised 

paragraph (i) of this AD to clarify the 

inspection requirements. No additional 

action is necessary for operators that 

have already complied with paragraph 

(i) of this AD. 

Request To Clarify Certain Language in 

Paragraph (j) of the Proposed AD 

Boeing also asked that we clarify the 

language in the restatement of actions 

specified in paragraph (j) of the 

proposed AD in order to specify that the 

inspections in paragraph (i) of the 

proposed AD can only be deferred for 

4,000 flight cycles if the upper inboard 

chord is replaced with a new chord. 

Boeing stated that changing paragraph 

(i) of the proposed AD ensures that it is 

clear that the inspection can only be 

deferred for 4,000 flight cycles if the 

upper inboard chord is replaced. 

We agree with the commenter for the 

reason provided. We have changed 

paragraph (j) of this AD to specify ‘‘For 

airplanes on which the rear spar upper 

inner chord is replaced with a new 

chord . . . :’’ 

Request To Clarify Certain Language in 

Paragraph (q) of the Proposed AD 

Boeing also asked that we clarify the 

language in the new actions specified in 

paragraph (q) of the proposed AD. 

Boeing stated that paragraph (j) of the 

proposed AD states when to resume the 

inspections after the chord is replaced. 

Boeing added that paragraph (i) of the 

proposed AD states the type of 

inspection and the repetitive inspection 

interval. Therefore, Boeing stated that 

paragraph (q) of the proposed AD 

should point to paragraph (i) of the 

proposed AD. 

We agree to clarify paragraph (q) of 

this AD. As noted above, paragraph (j) 

of the this AD specifies inspecting the 

new chord within 4,000 flight cycles 

after the chord replacement, as required 

by paragraph (i) of this AD, and 

repeating the inspections thereafter at 

the times specified in paragraph (i) of 

this AD. Therefore, we have included 

similar language in paragraph (q) of this 

AD. 

Request To Clarify Service Information 

References 

In addition, Boeing asked that we 

include 707 in the title for ‘‘Boeing 

Service Bulletin 3381,’’ as identified in 

paragraphs (k) and (l) of the proposed 

AD, to be consistent with all the other 

service information references in the 

NPRM. 

We agree with the commenter for the 

reasons provided. We have changed the 

service information references in 

paragraphs (k)(3)(i) and (l) of this AD to 

specify ‘‘Boeing 707 Service Bulletin 

3381.’’ 

Boeing also asked that we change the 

semi-colon (located between the service 

information references) in paragraph 

(k)(3)(ii) of the proposed AD to a 

comma, because it breaks up the 

sentence in an unintended way. 

We do not agree to change the semicolon in paragraph (k)(3)(ii) of this AD. 

In ADs, we use a semi-colon to separate 

service information references, except in 

cases where the semi-colon between 

service information might cause 

confusion, e.g., a sentence that already 

uses semi-colons between text other 

than the service information. The semicolon in paragraph (k)(3)(ii) of this AD 

does not change the intent of that 

paragraph. We have not changed this 

AD in this regard. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously, 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing 707 Alert Service 

Bulletin A3515, Revision 1, dated 

October 10, 2014. The service 


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information describes procedures for 

incorporating a new cycle counting 

procedure, determining the material for 

the horizontal stabilizer rear spar chord 

segment, inspecting for stress corrosion 

cracking and fatigue cracking, repair, 

and replacing all chord segments made 

of 7079 aluminum with new, improved 

chord segments made of 7075 

aluminum. This service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 10 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

TABLE—ESTIMATED COSTS

Action Work hours Parts Cost per product Fleet cost 

Retained inspections 

from AD 2012–17– 

13.

Up to 32 work-hours × $85 per hour = up 

to $2,720 per inspection cycle.

$0 .............................. Up to $2,720 per inspection cycle.Up to $27,200 per inspection cycle. 

Replacement [new action].500 work-hours × $85 per work-hour = 

$42,500 per chord.

Up to $228,000 per 

chord.

Up to $2,705,000 (up 

to 10 chords per 

airplane) 1.

Up to $27,050,000.2

1The 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. 2The 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2012–17–13, Amendment 39–17176 (77 

FR 55681, September 11, 2012), and 

adding the following new AD: 

2016–08–11 The Boeing Company: 

Amendment 39–18487; Docket No. 

FAA–2015–2965; Directorate Identifier 

2014–NM–227–AD. 

(a) Effective Date 

This AD is effective May 27, 2016. 

(b) Affected ADs 

This AD replaces AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012). 

(c) Applicability 

This AD applies to The Boeing Company 

airplanes, certificated in any category; 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model 707 airplanes identified in 

Boeing 707 Alert Service Bulletin A3515, 

Revision 1, dated October 10, 2014. 

(2) Model 720 and 720B series airplanes 

identified in Boeing 707 Alert Service 

Bulletin A3516, dated April 4, 2008. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by a determination 

that all chord segments made of 7079 

aluminum must be replaced with new, 

improved chord segments made of 7075 

aluminum. We are issuing this AD to detect 

and correct stress corrosion and potential 

early fatigue cracking in the horizontal 

stabilizer, which could result in reduced 

structural integrity of the horizontal 

stabilizer. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Flight Cycle Counting 

Procedure, With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. Flight cycles, as used in this 

AD, must be counted as defined in the 

service information identified in paragraph 

(g)(1), (g)(2), or (g)(3) of this AD. 

(1) Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007 (for Model 

707 airplanes). 

(2) Boeing 707 Alert Service Bulletin 

A3515, Revision 1, dated October 10, 2014 

(for Model 707 airplanes). 

(3) Boeing 707 Alert Service Bulletin 

A3516, dated April 4, 2008 (for Model 707 

airplanes, and Model 720 and 720B series 

airplanes). 


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Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 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 


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actions required by this paragraph in 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007; or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014, except as required by 

paragraph (n) of this AD. Do all applicable 

modifications before further flight. 

(ii) Replace the chord with a new chord, 

in accordance with Part 6 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007; or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014. 

(l) Retained Modification/Chord 

Replacement, With Revised Service 

Information 

This paragraph restates the actions 

required by paragraph (l) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. For airplanes identified in 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007; or Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014, with horizontal 

stabilizers that have rear spar chord 

components made from 7079 aluminum and 

have not had embodied the modification of 

Part II of Boeing 707 Service Bulletin 3381, 

dated July 25, 1980; or Boeing 707 Service 

Bulletin 3381, Revision 1, dated July 31, 

1981: Before further flight after determining 

the type of material in accordance with 

paragraph (h) of this AD, modify all 7079 

chord segments installed on the horizontal 

stabilizer, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007; or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014; or replace the chord, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007; or Boeing 707 Alert 

Service Bulletin A3515, Revision 1, dated 

October 10, 2014. 

(m) Retained Supplemental Structural 

Inspection Document Inspections 

This paragraph restates the actions 

required by paragraph (m) of AD 2012–17– 

13, Amendment 39–17176 (77 FR 55681, 

September 11, 2012). For all airplanes: 

Within 180 days or 1,000 flight cycles after 

October 16, 2012 (the effective date of AD 

2012–17–13), whichever occurs first, do the 

inspections of the applicable structurally 

significant items specified in and in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3516, dated April 4, 2008. If any 

cracking is found, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (r) of 

this AD. The inspections required by AD 85– 

12–01 R1, Amendment 39–5439 (51 FR 

36002, October 8, 1986), are still required, 

except, as of October 16, 2012 (the effective 

date of AD 2012–17–13), the flight cycle 

interval for the repetitive inspections 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing 707 Alert Service Bulletin A3516, 

dated April 4, 2008, must be counted in 

accordance with the requirements of 

paragraph (g) of this AD. 

(n) Retained Exception to Certain Service 

Information: Contacting FAA for Crack 

Repair 

This paragraph restates the actions 

required by paragraph (n) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. If any cracking is found during 

any inspection required by this AD, and 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007; or Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (r) of this AD. 

(o) Retained Exception to Certain Service 

Information: Nondestructive Test 

Compliance Procedures 

This paragraph restates the requirements of 

paragraph (o) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. Where Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007; or 

Boeing 707 Alert Service Bulletin A3515, 

Revision 1, dated October 10, 2014, specifies 

that operators ‘‘refer to’’ nondestructive test 

(NDT) procedures, the procedures must be 

done in accordance with the service 

information identified in paragraphs (o)(1), 

(o)(2), and (o)(3) of this AD, as applicable. 

(1) Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Subject 51– 

00–00, ‘‘Structures-General,’’ of Part 6—Eddy 

Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. 

(2) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6—Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. 

(3) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1—General, 

of the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. 

(p) Retained Parts Installation Prohibition 

With Revised Service Information 

This paragraph restates the parts 

installation prohibition required by 

paragraph (p) of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), with revised service 

information. As of October 16, 2012 (the 

effective date of AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012)), no person may install 

any horizontal stabilizer assembly with any 

chord segment having a part number other 

than that identified in paragraph 2.C.2. of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007; or Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014, on any airplane. 

(q) New Replacement of 7079 Aluminum 

Components 

Within 48 months after the effective date 

of this AD: Replace all 7079 aluminum chord 

segments of the upper and lower chords 

installed on the horizontal stabilizer with 

7075 aluminum chord segments, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, Revision 1, 

dated October 10, 2014. Within 4,000 flight 

cycles after accomplishing the replacements 

required by this paragraph, inspect the new 

chord, as required by paragraph (i) of this 

AD, and repeat the inspections thereafter at 

the times specified in paragraph (i) of this 

AD. 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (s) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2012–17–13, 

Amendment 39–17176 (77 FR 55681, 

September 11, 2012), are approved as 

AMOCs for the corresponding provisions of 

this AD. 

(s) Related Information 

For more information about this AD, 

contact Chandra Ramdoss, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles ACO, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5239; fax: 562–627–5210; 

email: chandraduth.ramdoss@faa.gov. 

(t) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing 707 Alert Service Bulletin 

A3515, Revision 1, dated October 10, 2014. 


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Federal Register / Vol. 81, No. 78 / Friday, April 22, 2016 / Rules and Regulations 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, ‘‘StructuresGeneral,’’ Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Part 6— 

Eddy Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. The 

revision level of this document is identified 

on only the manual revision Transmittal 

Sheet. 

(iv) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1—General, 

of the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. The revision level of this 

document is identified on only the manual 

revision Transmittal Sheet. 

(v) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6—Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. The revision level of this 

document is identified on only the manual 

revision Transmittal Sheet. 

(4) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800–0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https://

www.myboeingfleet.com. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on April 5, 

2016. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08539 Filed 4–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2015–5194; Airspace 

Docket No. 15–ACE–6] 

Establishment of Class E Airspace; 

Coldwater, KS 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E airspace in Coldwater, KS. Controlled 

airspace is necessary to accommodate 

new Standard Instrument Approach 

Procedures (SIAPs) at Comanche County 

Airport. The FAA is taking this action 

to enhance the safety and management 

of Instrument Flight Rule (IFR) 

operations at the airport. Additionally, 

to this action corrects the spelling of the 

airport name to Comanche County 

Airport, inadvertently misspelled in the 

proposal. 

DATES: Effective 0901 UTC, July 21, 

2016. The Director of the Federal 

Register approves this incorporation by 

reference action under title 1, Code of 

Federal Regulations, part 51, subject to 

the annual revision of FAA Order 

7400.9 and publication of conforming 

amendments. 

ADDRESSES: FAA Order 7400.9Z, 

Airspace Designations and Reporting 

Points, and subsequent amendments can 

be viewed on line at http://

www.faa.gov/airtraffic/publications/. 

For further information, you can contact 

the Airspace Policy Group, Federal 

Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: 202– 

267–8783. The Order is also available 

for inspection at the National Archives 

and Records Administration (NARA). 

For information on the availability of 

this material at NARA, call 202–741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federalregulations/ibr_locations.html. 

FAA Order 7400.9, Airspace 

Designations and Reporting Points, is 

published yearly and effective on 

September 15. 

FOR FURTHER INFORMATION CONTACT: 

Rebecca Shelby, Central Service Center, 

Operations Support Group, Federal 

Aviation Administration, Southwest 

Region, 10101 Hillwood Parkway, Fort 

Worth, TX 76177; telephone: (817) 222– 

5857. 

SUPPLEMENTARY INFORMATION: 

Authority for This Rulemaking 

The FAA’s authority to issue rules 

regarding aviation safety is found in 

Title 49 of the United States Code. 

Subtitle I, Section 106 describes the 

authority of the FAA Administrator. 

Subtitle VII, Aviation Programs, 

describes in more detail the scope of the 

agency’s authority. This rulemaking is 

promulgated under the authority 

described in Subtitle VII, Part, A, 

Subpart I, Section 40103. Under that 

section, the FAA is charged with 

prescribing regulations to assign the use 

of airspace necessary to ensure the 

safety of aircraft and the efficient use of 

airspace. This regulation is within the 

scope of that authority as it establishes 

controlled airspace at Comanche County 

Airport, Coldwater, KS. 

History 

On February 11, 2016, the FAA 

published in the Federal Register a 

notice of proposed rulemaking (NPRM) 

to establish Class E Airspace in the 

Coldwater, KS area. (81 FR 7251) FAA 

2015–5194. Interested parties were 

invited to participate in this rulemaking 

effort by submitting written comments 

on the proposal to the FAA. No 

comments were received. 

Class E airspace designations are 

published in paragraph 6005 of FAA 

Order 7400.9Z dated August 6, 2015, 

and effective September 15, 2015, which 

is incorporated by reference in 14 CFR 

part 71.1. The Class E airspace 

designations listed in this document 

will be published subsequently in the 

Order. 

Availability and Summary of 

Documents for Incorporation by 

Reference 

This document amends FAA Order 

7400.9Z, airspace Designations and 

Reporting Points, dated August 6, 2015, 

and effective September 15, 2015. FAA 

Order 7400.9Z is publicly available as 

listed in the ADDRESSES section of this 

document. FAA Order 7400.9Z lists 

Class A, B, C, D, and E airspace areas, 

air traffic service routes, and reporting 

points. 

The Rule 

This amendment to Title 14, Code of 

Federal Regulations (14 CFR) part 71 

establishes Class E airspace extending 

upward from 700 feet above the surface 

within a 7.5-mile radius of Comanche 

County Airport, Coldwater, KS, to 

accommodate new standard instrument 

approach procedures. Controlled 

airspace is needed for the safety and 

management of IFR operations at the 

airport. Additionally, the airport name 

is corrected from Commanche County 

Airport to Comanche County Airport. 

Class E airspace designations are 

published in Paragraph 6005 of FAA 

Order 7400.9Z, dated August 6, 2015, 

and effective September 15, 2015, which 

is incorporated by reference in 14 CFR 

71.1. The Class E airspace designations 

listed in this document will be 

published subsequently in the Order. 

Regulatory Notices and Analyses 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 


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