Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45453 

• Email: ConventionalCooking

Products2014STD0005@ee.doe.gov. 

Include the docket number EERE–2014– 

BT–STD–0005 in the subject line of the 

message. 

• Mail: Ms. Brenda Edwards, U.S. 

Department of Energy, Building 

Technologies Program, Mailstop EE–5B, 

Notice of Proposed Rulemaking for 

Energy Conservation Standards for 

Residential Conventional Ovens, Docket 

No. EERE–2014–BT–STD–0014, 1000 

Independence Avenue SW., 

Washington, DC 20585–0121. If 

possible, please submit all items on a 

CD. It is not necessary to include 

printed copies. 

• Hand Delivery/Courier: Ms. Brenda 

Edwards, U.S. Department of Energy, 

Building Technologies Program, 950 

L’Enfant Plaza SW., Suite 600, 

Washington, DC 20024. Telephone (202) 

586–2945. If possible, please submit all 

items on a CD, in which case it is not 

necessary to include printed copies. 

Instructions: All submissions received 

must include the agency name and 

docket number for this rulemaking. No 

telefacsimiles (faxes) will be accepted. 

Docket: The docket is available for 

review at www.regulations.gov, 

including Federal Register notices, 

comments, and other supporting 

documents/materials. All documents in 

the docket are listed in the 

www.regulations.gov index. However, 

not all documents listed in the index 

may be publicly available, such as 

information that is exempt from public 

disclosure. 

A link to the docket Web page can be 

found at: http://www.regulations.gov/

#!documentDetail;D=EERE-2014-BTSTD-0005-0014. This Web page contains 

a link to the docket for this notice on the 

regulation.gov site. The 

www.regulations.gov Web page contains 

instructions on how to access all 

documents in the docket, including 

public comments. 

FOR FURTHER INFORMATION CONTACT: 

Mr. John Cymbalsky, U.S. Department of 

Energy, Office of Energy Efficiency 

and Renewable Energy, Building 

Technologies Program, EE–2J, 1000 

Independence Avenue SW., 

Washington, DC 20585–0121. 

Telephone: (202) 287–1692. Email: 

kitchen_ranges_and_ovens@

ee.doe.gov. 

Ms. Celia Sher, U.S. Department of 

Energy, Office of the General Counsel, 

GC–33, 1000 Independence Avenue 

SW., Washington, DC 20585–0121. 

Telephone: (202) 287–6122. Email: 

Celia.Sher@hq.doe.gov. 

SUPPLEMENTARY INFORMATION: On June 

10, 2015, DOE published a notice of 

proposed rulemaking (NOPR) and 

public meeting in the Federal Register 

that proposed new and amended energy 

conservation standards for residential 

conventional ovens. 80 FR 33030. The 

NOPR requested comment from the 

public on the proposed standards, 

associated analyses, and results, and 

provided for the written submission of 

comments by August 10, 2015. The 

Association of Home Appliance 

Manufacturers (AHAM) requested that 

DOE extend the comment period by 60 

days so that manufacturers can obtain 

sufficient data to fully analyze DOE’s 

proposed rule according to the 

conventional oven test procedure final 

rule that was published on July 2, 2015. 

80 FR 37954. Because there are 

currently no performance based energy 

conservation standards, AHAM noted 

that manufacturers do not conduct 

regular energy tests on conventional 

ovens. AHAM further stated that by 

allowing additional time for 

manufacturers (and other stakeholders 

who wish to conduct testing) to test 

their products, manufacturers will be 

able to provide key data to support 

DOE’s analysis. 

Based on AHAM’s request, DOE 

determines that a 30 day extension of 

the public comment period is 

appropriate to allow interested parties 

additional time to submit comments. 

DOE notes that it issued and made 

available a pre-publication version of 

the conventional oven test procedure 

final rule on June 9, 2015. Based on 

DOE’s testing experience, extending the 

comment period by 30 days for a 90 day 

total period should be sufficient time for 

manufacturers to conduct testing using 

the new oven test procedure and 

aggregate results. DOE will consider any 

comments received by midnight of 

September 9, 2015 to be timely 

submitted. 

Issued in Washington, DC, on July 23, 

2015. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2015–18687 Filed 7–29–15; 8:45 am] 

BILLING CODE 6450–01–P 

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). 

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. 


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• 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

Action Work hours Parts Cost per product Fleet cost 

Retained inspections from AD 2012– 

17–13, Amendment 39–17176 (77 

FR 55681, September 11, 2012).

Up to 32 work-hours X $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 


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Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 45455 

TABLE—ESTIMATED COSTS—Continued 

Action Work hours Parts Cost per product Fleet cost 

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

= $42,500.

Up to $228,000 

per chord.

Up to $2,322,500 

(up to 10 chords 

per airplane) 1.

Up to 

$23,225,000 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 

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 

■ 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: 

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 


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45456 Federal Register / Vol. 80, No. 146 / Thursday, July 30, 2015 / Proposed Rules 

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 


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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-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 

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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2964; Directorate 

Identifier 2014–NM–206–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A319, A320, and A321 

series airplanes. This proposed AD is 

intended to complete certain mandated 

programs intended to support the 

airplane reaching its limit of validity 

(LOV) of the engineering data that 

support the established structural 

maintenance program. This proposed 

AD would require reinforcing the 

forward pressure bulkhead at a certain 

stringer on both the left-hand and righthand sides, and related investigative 

and corrective actions if necessary. We 

are proposing this AD to prevent fatigue 

cracking of the forward pressure 


Lhorne on DSK7TPTVN1PROD with PROPOSALS