Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 46543 

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 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18564 Filed 7–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0665; Directorate 

Identifier 2012–NM–082–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 A330–300 series airplanes 

and Model A340–200 and –300 series 

airplanes. This proposed AD was 

prompted by reports of corrosion found 

on certain trimmable horizontal 

stabilizer actuators (THSA), affecting the 

ballscrew lower splines between the tie 

bar and the screw-jack. This proposed 

AD would require repetitive detailed 

inspections for corrosion of certain 

THSAs, ballscrew integrity tests if 

necessary; and replacing any affected 

THSA with a serviceable or new and 

improved THSA, if necessary. We are 

proposing this AD to detect and correct 

corrosion of the THSAs, which could 

lead, in the case of ballscrew rupture, to 

the loss of transmission of THSA torque 

loads from the ballscrew to the tie-bar, 

prompting THSA blowback, and 

possibly resulting in loss of control of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by September 16, 

2013. 

ADDRESSES: You may send comments 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. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. For Goodrich service 

information identified in this proposed 

AD, contact Goodrich Corporation, 

Actuation Systems, Product Support 

Department 13, Avenue de 

L’Eguillette—Saint-Ouen L’Aumone 

Boite Postale 7186 95056, Cergy 

Pontoise Cedex, France; fax: 33–1– 

34326310. You may review copies of the 

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; or in person at the 

Docket Operations office 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 Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–1138; 

fax (425) 227–1149. 

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–2013–0665; Directorate Identifier 

2012–NM–082–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 based on 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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0061R1, 

dated November 30, 2012 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Some Trimmable Horizontal Stabilizer 

Actuators (THSA), Part Number (P/N) 47147– 

500, have been found with corrosion, 

affecting the ballscrew lower splines between 

the tie bar and the screw-jack. 

The results of the technical investigations 

have identified that the corrosion was caused 

by a combination of: 

—Contact/friction between the tie bar and the 

inner surface of the ballscrew leading to 

the removal of Molykote (corrosion 

protection) at the level of the tie bar 

splines, 

—Humidity ingress initiating surface 

oxidation starting from areas where 

Molykote is removed, and 

—Water retention in THSA lower part 

leading to corrosion spread out and to the 

creation of a brown deposit (iron oxide). 

The results of the technical investigations 

have also concluded that THSA P/N 47147– 

500 and P/N 47147–700 ballscrews might be 

affected by this corrosion issue. 

THSA P/N 47147–400 ballscrews might be 

affected as well, but should no longer be in 

service, and modified into P/N 47147–500, as 

required by EASA AD 2010–0192 and EASA 

AD 2010–0193 [and as required by FAA AD 

2005–07–04, Amendment 39–14028 (70 FR 

16104, March 30, 2005)]. 

This condition, if not detected and 

corrected, may lead, in case of ballscrew 

rupture, to loss of transmission of THSA 

torque loads from the ballscrew to the tie-bar, 

prompting THSA blowback, possibly 

resulting in loss of control of the aeroplane. 

To correct this potential unsafe condition, 

EASA issued AD 2012–0061 to require 

repetitive [detailed] visual inspections of the 

ballscrew lower splines of THSA having 

P/N 47147–500 or P/N 47147–700 to detect 

corrosion and, depending on findings 

[ballscrew integrity tests], the 

accomplishment of applicable corrective 

actions [replacing the affected THSA with a 

serviceable or improved THSA]. 

Since that [EASA] AD [2012–0061] was 

issued, Airbus published new Service 

Bulletin (SB) A330–27–3194 or Airbus SB 

A340–27–4187 (Airbus modification 202802), 

which allow installation in service of an 

improved THSA P/N 47172–530. 

For the reasons described above, this 

[EASA] AD [2012–0061R1] is revised to 

specify that installation of THSA P/N 47172– 


emcdonald on DSK67QTVN1PROD with PROPOSALS
46544 Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 

530 is an alternative (optional) terminating 

action to the repetitive inspections required 

by this AD. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued the following 

service information. 

• Airbus Mandatory Service Bulletin 

A330–27–3179, including Appendix 01, 

dated February 14, 2012. 

• Airbus Service Bulletin A330–27– 

3182, dated February 14, 2012. 

• Airbus Service Bulletin A330–27– 

3194, dated October 8, 2012. 

• Airbus Mandatory Service Bulletin 

A340–27–4175, including Appendix 01, 

dated February 14, 2012. 

• Airbus Service Bulletin A340–27– 

4178, dated February 14, 2012. 

• Airbus Service Bulletin A340–27– 

4187, dated October 8, 2012. 

Goodrich Actuation Systems has 

issued Service Bulletin 47147–27–18, 

dated February 17, 2012. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 30 products of U.S. registry. 

We also estimate that it would take 

about 6 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$15,300, or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 13 work-hours and require parts 

costing up to $722,556 for a cost of up 

to $723,661 per product. We have no 

way of determining the number of 

products that may need these actions. 

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 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 this 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 adding 

the following new AD: 

Airbus: Docket No. FAA–2013–0665; 

Directorate Identifier 2012–NM–082–AD. 

(a) Comments Due Date 

We must receive comments by September 

16, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by reports of 

corrosion found on certain trimmable 

horizontal stabilizer actuators (THSA), 

affecting the ballscrew lower splines between 

the tie bar and the screw-jack. We are issuing 

this AD to detect and correct corrosion of the 

THSAs, which could lead, in the case of 

ballscrew rupture, to loss of transmission of 

THSA torque loads from the ballscrew to the 

tie-bar, prompting THSA blowback, and 

possibly resulting in loss of control of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1) or (g)(2) of this AD, except 

as required by paragraphs (h)(1) and (h)(2) of 

this AD: Do a detailed inspection of the gaps 

between the screw shaft and tie rod teeth of 

any THSA having part numbers (P/N) 47147– 

500 and 47147–700, to determine if the 

corrosion condition is Type I, Type II, or 

Type III, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179 

(for Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes); 

or A340–27–4175 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes); 

both dated February 14, 2012; and the 

Accomplishment Instructions and flowchart 

following the Accomplishment Instructions 

of Goodrich Actuation Systems Service 

Bulletin 47147–27–18, dated February 17, 

2012. Repeat the inspection thereafter at 

intervals not to exceed 24 months until the 


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Federal Register / Vol. 78, No. 148 / Thursday, August 1, 2013 / Proposed Rules 46545 

modification specified in paragraph (k) is 

done. 

(1) For any THSA, which, as of the 

effective date of this AD, has accumulated 

less than 156 months since first flight on an 

airplane as THSA P/N 47147–400 or since its 

first flight after modification has been done 

as specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3052 or A340–27–4059: 

Do the inspection before the accumulation of 

156 months but not before the accumulation 

of 132 months since first flight on an airplane 

as THSA P/N 47147–400 or since the THSA 

first flight after its modification was done as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3052 or A340–27–4059; or 

within 3 months after the effective date of 

this AD; whichever occurs later. 

(2) For any THSA, which, as of the 

effective date of this AD, has accumulated 

156 months or more since first flight on an 

airplane as THSA P/N 47147–400 or since 

the THSA first flight after modification has 

been done as specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3052 

or A340–27–4059: Do the inspection within 

3 months after the effective date of this AD. 

(h) Compliance Time Exceptions 

(1) Some THSAs having P/N 47147–500 

(and further derivative with P/N 47147–700) 

were originally THSA P/N 47147–400 and 

were subsequently modified in service. In 

this case, the time accumulated by any THSA 

must be calculated from the first installation 

on airplanes as THSA P/N 47147–400. 

(2) Some THSAs having P/N 47147–500 

(and further derivative with P/N 47147–700) 

were originally THSA P/N 47147–200, –210, 

–213, –300, –303, or –350 and were 

subsequently modified in service as specified 

in the Accomplishment Instructions of 

Airbus Mandatory Service Bulletin A330–27– 

3052 or A340–27–4059. In this case, the time 

accumulated by any THSA must be 

calculated from the first flight on an airplane 

after the THSA has been modified as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3052 or A340–27–4059. 

(i) Ballscrew Integrity Test and Corrective 

Actions 

If, during any inspection required by 

paragraph (g) of this AD, it is determined that 

a THSA has Type II or Type III corrosion, 

before further flight: Do a ballscrew integrity 

test, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179 (for Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes); or A340–27–4175 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes); both dated 

February 14, 2012. 

(1) For THSAs having Type II or Type III 

corrosion, and the results of the ballscrew 

integrity test were not correct, as specified in 

the Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179 

(for Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes); 

or A340–27–4175 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes); 

both dated February 14, 2012: Before further 

flight, replace the affected THSA with a new 

or serviceable THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179 

(for Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes); 

or A340–27–4175 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes); 

both dated February 14, 2012. 

(2) For THSAs having Type III corrosion, 

and the results of the ballscrew integrity test 

are correct, as specified in the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3179 

(for Model A330–301, –302, –303, –321, 

–322, –323, –341, –342, and –343 airplanes); 

or A340–27–4175 (for Model A340–211, 

–212, –213, –311, –312, and –313 airplanes); 

both dated February 14, 2012: Within 10 days 

after the most recent inspection, replace the 

THSA with a new or serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179 (for Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes); or A340–27–4175 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes); both dated 

February 14, 2012. 

(3) For THSAs having Type II corrosion 

and the results of the ballscrew integrity test 

are correct: Within 24 months or 4,400 flight 

cycles after the most recent inspection, 

whichever occurs first, replace the THSA 

with a new or serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3179 (for Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes); or A340–27–4175 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes); both dated 

February 14, 2012. 

(j) Replacement of a THSA Is Not 

Terminating Action 

Replacement of a THSA with a THSA 

having P/N 47147–500 or 47147–700 does 

not constitute a terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(k) Optional Terminating Modification 

(1) Replacing any THSA having P/N 

47147–500 with a new improved THSA 

having P/N 47172–300 (Airbus modification 

200238), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3182 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4178 (for Model A340–211, –212, –213, 

–311, –312, and –313 airplanes); both dated 

February 14, 2012; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(2) Replacing any THSA having P/N 

47147–700 with a new improved THSA 

having P/N 47172–530 (Airbus modification 

202802), in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–27–3194 (for Model 

A330–301, –302, –303, –321, –322, –323, 

–341, –342, and –343 airplanes); or A340– 

27–4187 (for Model A340–211, –212, –213, 

–311, –312, and –313 airplanes); both dated 

October 8, 2012; terminates the repetitive 

inspections required by paragraph (g) of this 

AD. 

(l) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install a THSA, P/N 47147–500 

or P/N 47147–700, on any airplane, unless 

the THSA is classified as Type I (no 

corrosion), in accordance with the criteria 

defined in Goodrich Actuation Systems 

Service Bulletin 47147–27–18, dated 

February 17, 2012; and thereafter inspected 

in accordance with the requirements of 

paragraph (g) of this AD and any applicable 

actions required by paragraph (i) of this AD 

are accomplished. 

(m) Reporting 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g) of this AD to 

Airbus, at the applicable time specified in 

paragraph (m)(1) or (m)(2) of this AD, using 

Appendix 01 of Airbus Mandatory Service 

Bulletins A330–27–3179 (for Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes); or A340–27–4175 

(for Model A340–211, –212, –213, –311, 

–312, and –313 airplanes); both dated 

February 14, 2012. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, 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 International Branch, send it 

to ATTN: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 


emcdonald on DSK67QTVN1PROD with PROPOSALS
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(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(o) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0061R1, dated November 30, 2012; and the 

service information identified in paragraphs 

(o)(1)(i) through (o)(1)(vii) of this AD; for 

related information. 

(i) Airbus Mandatory Service Bulletin 

A330–27–3179, dated February 14, 2012. 

(ii) Airbus Service Bulletin A330–27–3182, 

dated February 14, 2012. 

(iii) Airbus Service Bulletin A330–27– 

3194, dated October 8, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A340–27–4175, dated February 14, 2012. 

(v) Airbus Service Bulletin A340–27–4178, 

dated February 14, 2012. 

(vi) Airbus Service Bulletin A340–27– 

4187, dated October 8, 2012. 

(vii) Goodrich Actuation Systems Service 

Bulletin 47147–27–18, dated February 17, 

2012. 

(2) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. For Goodrich Actuation 

Systems service information identified in this 

AD, contact Goodrich Corporation, Actuation 

Systems, Product Support Department 13, 

Avenue de L’Eguillette—Saint-Ouen 

L’Aumone Boite Postale 7186 95056, Cergy 

Pontoise Cedex, France; fax: 33–1–34326310. 

You may review copies of the 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 21, 

2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18566 Filed 7–31–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Highway Administration 

23 CFR Part 636 

[Docket No. FHWA–2013–0043] 

RIN 2125–AF58 

Design-Build Contracting 

AGENCY: Federal Highway 

Administration (FHWA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM); request for comments. 

SUMMARY: This NPRM provides 

interested parties with the opportunity 

to comment on proposed changes to the 

FHWA requirements related to the use 

of alternative technical concepts (ATC) 

in design-build project delivery of 

highway construction. The revisions are 

intended to eliminate the requirement to 

submit a base proposal when a 

contracting agency allows design-build 

proposers to submit ATCs in their 

technical and price proposals. The 

FHWA seeks comments on the 

proposals contained in this notice. 

DATES: Comments must be received on 

or before September 30, 2013. Late 

comments will be considered to the 

extent practicable. 

ADDRESSES: Mail or hand deliver 

comments to the U.S. Department of 

Transportation, Dockets Management 

Facility, Room W12–140, 1200 New 

Jersey Avenue SE., Washington, DC 

20590, or fax comments to (202) 493– 

2251. Alternatively, comments may be 

submitted via the Federal eRulemaking 

Portal at http://www.regulations.gov 

(follow the on-line instructions for 

submitting comments). 

All comments should include the 

docket number that appears in the 

heading of this document. All 

comments received will be available for 

examination and copying at the above 

address from 9 a.m. to 5 p.m., e.t., 

Monday through Friday, except Federal 

holidays. Those desiring notification of 

receipt of comments must include a selfaddressed, stamped postcard or you 

may print the acknowledgment page 

that appears after submitting comments 

electronically. All comments received 

into any docket may be searched in 

electronic format by the name of the 

individual submitting the comment (or 

signing the comment, if submitted on 

behalf of an association, business, labor 

union, etc.). Persons making comments 

may review DOT’s complete Privacy Act 

Statement in the Federal Register 

published on April 11, 2000 (Volume 

65, Number 70, Pages 19477–78), or you 

may view the statement at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: Mr. 

Gerald Yakowenko, Contract 

Administration Team Leader, Office of 

Program Administration, (202) 366– 

2221, or Mr. Michael Harkins, Office of 

the Chief Counsel, (202) 366–4928, 

Federal Highway Administration, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. Office hours for the FHWA 

are from 8:00 a.m. to 4:30 p.m., e.t., 

Monday through Friday, except Federal 

holidays. 

SUPPLEMENTARY INFORMATION: 

Electronic Access and Filing 

You may submit or retrieve comments 

online through the Federal eRulemaking 

portal at: http:www.regulations.gov. The 

Web site is available 24 hours each day 

of the year. Electronic submission and 

retrieval help and guidelines are 

available under the help section of the 

Web site. 

An electronic copy of this document 

may also be downloaded from the Office 

of the Federal Register’s home page at: 

http://www.archives.gov/federal_register 

and the Government Printing Office’s 

Web page at: http://www.gpoaccess.gov. 

Background 

Over the past 20 years, contracting 

agencies have been gaining valuable 

experience with the design-build project 

delivery method for highway 

construction. In conjunction with this 

delivery method, some agencies have 

encouraged design-build proposers to 

submit ATCs as a way to encourage 

innovation, promote efficiency, reduce 

risk, accelerate project delivery 

schedules, and reduce project costs. 

An ATC is a request by a proposer to 

modify a contract requirement, 

specifically for that proposer’s use in 

the proposal process. The ATC must 

provide a solution that is equal or better 

to the requirements in the Request for 

Proposals (RFP) document. Proposers 

submit ATCs for the contracting 

agency’s conceptual approval during the 

procurement process. The contracting 

agency may conduct confidential 

meetings with each proposer to review 

and discuss that proposer’s ATCs. If the 

concept is approved by the contracting 

agency, the proposer may use the ATC 

in its technical and price proposal, thus 

providing the contracting agency with 

the potential for increased value at 

reduced costs. 

The FHWA’s current regulatory policy 

in 23 CFR Part 636 allows contracting 

agencies to use ATCs in their 

procurement process subject to two 

conditions: (1) The ATC must not 


emcdonald on DSK67QTVN1PROD with PROPOSALS