28238 Federal Register / Vol. 77, No. 93 / Monday, May 14, 2012 / Rules and Regulations 

■ 6. Amend § 124.513(c)(4) by adding 

the word ‘‘populated’’ before the word 

‘‘separate.’’ 

■ 7. Amend § 124.519 by adding 

paragraphs (a)(1), (a)(2), and (a)(3) to 

read as follows: 

§ 124.519 Are there any dollar limits on the 

amount of 8(a) contracts that a Participant 

may receive? 

(a) * * * 

(1) For a firm having a receipts-based 

primary NAICS code at time of program 

entry, the limit above which it can no 

longer receive sole source 8(a) contracts 

is five times the size standard 

corresponding to its primary NAICS 

code which is determined as of the date 

of SBA’s acceptance of the requirement 

for the 8(a) BD program or $100,000,000, 

whichever is less. 

(2) For a firm having an employeebased primary NAICS code at time of 

program entry, the limit above which it 

can no longer receive sole source 8(a) 

contracts is $100,000,000. 

(3) SBA will not consider 8(a) 

contracts awarded under $100,000 in 

determining whether a Participant has 

reached the limit identified in 

paragraphs (a)(1) and (a)(2) of this 

section. 

* * * * * 

■ 8. Amend § 124.520 by revising 

paragraph (c)(3) to read as follows: 

§ 124.520 What are the rules governing 

SBA’s Mentor/Prote ́ge ́ program? 

* * * * * 

(c) * * * 

(3) A prote ́ge ́ firm may generally have 

only one mentor at a time. The AA/BD 

may approve a second mentor for a 

particular prote ́ge ́ firm where the 

second relationship will not compete or 

otherwise conflict with the business 

development assistance set forth in the 

first mentor/prote ́ge ́ relationship and 

either: 

(i) The second relationship pertains to 

a, secondary NAICS code; or 

(ii) The prote ́ge ́ firm is seeking to 

acquire a specific expertise that the first 

mentor does not possess. 

* * * * * 

Dated: May 4, 2012. 

A. John Shoraka, 

Associate Administrator for Government 

Contracting and Business Development. 

[FR Doc. 2012–11508 Filed 5–11–12; 8:45 am] 

BILLING CODE 8025–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0998; Directorate 

Identifier 2011–NM–046–AD; Amendment 

39–17042; AD 2012–09–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A319–111, –112, and 

–132 airplanes; Model A320–111, –211, 

–212, –214 and –232 airplanes; and 

Model A321–111, –211, –212, and –231 

airplanes. This AD was prompted by 

reports that corrosion was found on the 

overwing refueling aperture on the top 

wing skin, and that for certain airplanes, 

repairs made using primer coating may 

prevent proper electrical bonding 

provision between the overwing 

refueling cap adaptor and the wing skin. 

This AD requires performing an 

electrical bonding test between the 

gravity fill re-fuel adaptor and the top 

skin panels on the left-hand and righthand wings, and if necessary performing 

a general visual inspection for corrosion 

of the component interface and adjacent 

area, and repairing the gravity fuel 

adaptor if any corrosion is found. We 

are issuing this AD to detect and correct 

corrosion and improper bonding, which 

in combination with a lightning strike in 

this area, could create a source of 

ignition in a fuel tank, resulting in a fire 

or explosion, and consequent loss of the 

airplane. 

DATES: This AD becomes effective June 

18, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 18, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 5, 2011 (76 FR 

61641). That NPRM proposed to require 

correct an unsafe condition for the 

specified products. The MCAI states: 

Cases of corrosion findings have been 

reported on the overwing refueling aperture 

(used to fill the fuel tank by gravity) on the 

wing top skin. The reported corrosion was on 

the mating surface of the aperture flange, 

underneath the refuel adaptor. Corrosion 

findings have been repaired on a case by case 

basis in accordance with approved data. 

For certain aeroplanes (identified by MSN 

in the applicability section of this [European 

Aviation Safety Agency (EASA)] AD, the 

provided repair contained instructions to 

apply primer coating on the mating surface. 

Since doing those repairs, it has been found 

that this primer coating may prevent proper 

electrical bonding provision between the 

overwing refuelling cap adaptor and the wing 

skin. 

This condition, if not corrected, could, in 

combination with a lightning strike in this 

area, create a source of ignition in a fuel tank, 

possibly resulting in a fire or explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires a one-time electrical 

bonding check between the gravity fill re-fuel 

adaptor and the top skin panels on the 

affected aeroplanes and, in case of findings 

[a general visual inspection for corrosion of 

the component interface and adjacent area], 

the application of the associated corrective 

actions [i.e. repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Permit a Ferry Flight 

US Airways stated that there currently 

is no fly-back allowance in the NPRM 

(76 FR 61641, October 5, 2011). US 

Airways also stated that this makes it 

difficult for airlines to schedule the 

inspection quickly, which is the most 

desirable situation. 

We infer that US Airways is 

requesting a ferry flight permit. We 

partially agree with this request. Unless 

otherwise specified in the AD, special 

flight permits are currently allowed 

under section 39.23 of the Federal 

Aviation Regulations (14 CFR 39.23). No 

change is therefore necessary to the AD 

regarding this issue. 


emcdonald on DSK29S0YB1PROD with RULES
Federal Register / Vol. 77, No. 93 / Monday, May 14, 2012 / Rules and Regulations 28239 

Request That the FAA Accept Published 

Service Repair Manual (SRM) Repairs 

as an FAA-Approved Corrective Action 

for Compliance With the AD 

US Airways stated that it asked 

Airbus to provide an SRM repair for 

expected findings, and that it has been 

informed by Airbus that a repair design 

was expected to be published in the 

February 2012 revision of the SRM. US 

Airways requested that a statement in 

the final rule be added to acknowledge 

that published SRM repairs are a FAAapproved corrective action for the 

proposed AD (76 FR 61641, October 5, 

2011). 

We partially agree with US Airways’ 

request. We understand US Airways’ 

concern regarding the unavailability of 

repair procedures and its effect on their 

scheduling of repairs since a 

discrepancy requires repair before 

further flight. However, we cannot 

provide approval of future SRM repairs 

in an AD by using the phrase, ‘‘or later 

FAA-approved revisions,’’ because it 

violates the Office of the Federal 

Register regulations for approving 

materials that are incorporated by 

reference. However, we consider that 

service information (including SRM 

repair) approved by EASA (or its 

delegated agent) is equivalent to FAAapproved corrective action for this AD, 

if it meets the certification basis of the 

affected airplanes and mitigates the 

unsafe condition addressed in this AD. 

We have not changed this AD in this 

regard. 

Request To Revise the Costs of 

Compliance 

United Airlines requested that the 

‘‘Costs of Compliance’’ section of the 

NPRM (76 FR 61641, October 5, 2011) 

be revised. United Airlines stated that 

under the ‘‘Costs of Compliance’’ 

section in the NPRM, an estimate of 6 

work-hours is specified to comply with 

the NPRM. United Airlines stated that 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010, specifies a total of 

12.5 work-hours to accomplish this 

inspection. United Airlines stated that 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010, provides a more 

accurate representation of the workhours required for this task, and it 

requests that the FAA justify its 

proposed estimate of 6 work-hours 

required to comply with the NPRM. 

In addition, United Airlines stated 

that, when accomplishing paragraph 

(g)(2) of the NPRM (76 FR 61641, 

October 5, 2011), which requires 

performing a general visual inspection 

for corrosion if the resistance value is 

greater than 10 milliOhms, the operator 

is directed to section. 3.C.(2) of the 

Accomplishment Instructions, Subtask 

571152–832–401–001—Removal of 

Primer—Inspection for Corrosion, of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. United Airlines 

stated that this subtask’s ‘‘Manpower 

Resources’’ chart specifies that it takes 

‘‘5 man-hours and 2.5 hours elapsed 

time’’ to complete that part of that 

service bulletin, and that under this 

subtask, Step (a), among other actions, 

requires defueling and venting of the 

two fuel tanks. United Airlines also 

stated that operator experience has 

shown that this procedure alone takes 

about ‘‘8 man-hours and 4 hours of 

elapsed time.’’ United Airlines stated it 

understands that it is not standard 

practice to propose manufacturers’ 

service bulletin changes through the 

FAA, but it would like to offer a more 

accurate estimate of at least ‘‘10 manhours and 6 hours elapsed time,’’ in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin 

A320–57–1152, dated June 14, 2010. 

We agree with United Airlines’ 

request to revise the ‘‘Costs of 

Compliance’’ section of this AD. We 

have clarified the ‘‘Costs of 

Compliance’’ section by estimating that 

it would take about 2 work-hours to 

perform the initial action (electrical 

bonding test). In addition, we have 

estimated that it would take about 12 

work-hours to perform the follow-on 

actions (inspection for corrosion and 

repair). We have changed this AD 

accordingly. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed–except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

61641, October 5, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 61641, 

October 5, 2011). 

Costs of Compliance 

We estimate that this AD will affect 

67 products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements (electrical bonding 

test) of this AD. The average labor rate 

is $85 per work-hour. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $11,390, or 

$170 per product. 

In addition, we estimate that any 

necessary follow-on actions (inspection 

for corrosion and repair) would take 

about 12 work-hours and require parts 

costing $0, for a cost of $1,020 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 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 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 AD and placed it in the AD docket. 

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 


emcdonald on DSK29S0YB1PROD with RULES
28240 Federal Register / Vol. 77, No. 93 / Monday, May 14, 2012 / Rules and Regulations 

contains the NPRM (76 FR 61641, 

October 5, 2011), 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. 

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 adding 

the following new AD: 

2012–09–07 Airbus: Amendment 39–17042. 

Docket No. FAA–2011–0998; Directorate 

Identifier 2011–NM–046–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 18, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A319– 

111, –112, and –132 airplanes; Model A320– 

111, –211, –212, –214 and –232 airplanes; 

and Model A321–111, –211, –212, and –231 

airplanes; certificated in any category; having 

manufacturer serial numbers 0039, 0078, 

0109, 0118, 0120, 0153, 0174, 0187, 0203, 

0215, 0218, 0226, 0227, 0228, 0236, 0237, 

0269, 0270, 0278, 0285, 0286, 0287, 0288, 

0294, 0301, 0337, 0377, 0462, 0463, 0464, 

0465, 0520, 0523, 0528, 0876, 0888, 0921, 

0935, 0974, 1014, 1102, 1130, 1160, 1162, 

1177, 1215, 1250, 1287, 1336, 1388, 1404, 

1444, 1449, 1476, 1505, 1524, 1564, 1605, 

1616, 1622, 1640, 1645, 1658, 1677, 1691, 

1729, and 1905. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports that 

corrosion was found on the overwing 

refueling aperture on the top wing skin, and 

that for certain airplanes, repairs made using 

primer coating may prevent proper electrical 

bonding provision between the overwing 

refueling cap adaptor and the wing skin. We 

are issuing this AD to detect and correct 

corrosion and improper bonding, which in 

combination with a lightning strike in this 

area, could create a source of ignition in a 

fuel tank, resulting in a fire or explosion, and 

consequent loss 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) Electrical Bonding Test and General 

Visual Inspection if Necessary 

Within 24 months after the effective date 

of this AD, do an electrical bonding test to 

check for bonding between the re-fuel 

adaptor of the gravity fill and the top skin 

panels on the left-hand and right-hand wings, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010. 

(1) If the resistance value is 10 milliOhms 

or less at the left-hand and right-hand wing, 

no further action is required. 

(2) If the resistance value is greater than 10 

milliOhms at the left-hand or right-hand 

wing, before further flight, do a general visual 

inspection for corrosion of the component 

interface and adjacent area, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. If any corrosion is found 

during the inspection, before further flight, 

repair the gravity fill fuel adaptor, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

57–1152, dated June 14, 2010; except where 

Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010, specifies to contact 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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. 

(i) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0034, dated March 2, 2011; 

and Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010; for related information. 

(j) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Airbus Service Bulletin A320–57–1152, 

dated June 14, 2010. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call 202–741– 

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

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on April 30, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11027 Filed 5–11–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0993; Directorate 

Identifier 2011–NM–018–AD; Amendment 

39–17043; AD 2012–09–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200 

and –300 series airplanes. This AD was 


emcdonald on DSK29S0YB1PROD with RULES