Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 74597 

only to the Enterprises, which are not 

small entities for purposes of the 

Regulatory Flexibility Act. 

List of Subjects in 12 CFR Part 1251 

Administrative practice and 

procedure, Capital Magnet Fund, 

Government-sponsored enterprises, 

Housing Trust Fund, Reporting and 

recordkeeping requirements. 

Authority and Issuance 

Accordingly, for the reasons stated in 

the Supplementary Information, under 

the authority of 12 U.S.C. 4567, the 

Federal Housing Finance Agency 

amends Chapter XII of Title 12 of the 

Code of Federal Regulations, as follows: 

CHAPTER XII—FEDERAL HOUSING 

FINANCE AGENCY 

SUBCHAPTER C—ENTERPRISES 

■ 1. Add part 1251 to Subchapter C to 

read as follows: 

PART 1251—CONTRIBUTIONS TO THE 

HOUSING TRUST AND CAPITAL 

MAGNET FUNDS 

Sec. 

1251.1 Purpose. 

1251.2 Definitions. 

1251.3 Prohibition on pass-through of cost 

of allocation; enforcement. 

1251.4 Submission of information. 

Authority: 12 U.S.C. 1452(c), 1718(b), 

4511(b), 4513(a), 4514(a), 4526(a), and 4567. 

§ 1251.1 Purpose. 

The purpose of this part is to 

implement a prohibition against an 

Enterprise redirecting the cost of any 

allocation to the Housing Trust Fund or 

the Capital Magnet Fund to originators 

of mortgages purchased or securitized 

by an Enterprise. 

§ 1251.2 Definitions. 

The following definitions apply to the 

terms used in and related specifically to 

this part. Definitions of other terms may 

be found in 12 CFR part 1201, General 

Definitions Applying to All Federal 

Housing Finance Agency Regulations: 

Capital Magnet Fund means that 

Fund established at section 1339(a) of 

the Safety and Soundness Act, 12 U.S.C. 

4569(a). 

Housing Trust Fund means that Fund 

established by section 1338(a) of the 

Safety and Soundness Act, 12 U.S.C. 

4568(a). 

§ 1251.3 Prohibition on pass-through of 

cost of allocation; enforcement. 

(a) In general. No Enterprise shall redirect or pass through the cost of any 

allocation to the Housing Trust Fund or 

the Capital Magnet Fund required 

pursuant to section 1337(a) of the Safety 

and Soundness Act, 12 U.S.C. 4567(a), 

through increased charges or fees, or 

decreased premiums, or in any other 

manner, to the originators of mortgages 

purchased or securitized by the 

Enterprise. 

(b) Enforcement. Compliance by each 

Enterprise with the foregoing 

prohibition shall be enforced under 

subpart 3 of part B of the Safety and 

Soundness Act, 12 U.S.C. 4581–89. 

§ 1251.4 Submission of information. 

The Director may issue guidance, 

orders, or notices on compliance with 

section 1337 and this part by the 

Enterprises, which may include 

information submissions by the 

Enterprises. 

Dated: December 10, 2014. 

Melvin L. Watt, 

Director, Federal Housing Finance Agency. 

[FR Doc. 2014–29345 Filed 12–15–14; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0453; Directorate 

Identifier 2013–NM–205–AD; Amendment 

39–18049; AD 2014–25–07] 

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 A320–211, –212, –214, 

–231, –232, and –233 airplanes. This AD 

was prompted by a report of cracking at 

the splice plate of the frame (FR) 47 butt 

joint crossing area found during fullscale fatigue testing. This AD requires 

repetitive inspections for cracking of 

both sides of the splice plate of that 

frame butt joint crossing area, and 

corrective action if necessary. This AD 

also provides for an optional 

modification, which terminates the 

repetitive inspections. We are issuing 

this AD to detect and correct fatigue 

cracking of the splice plate of the FR 47 

butt joint crossing area, which could 

result in reduced structural integrity of 

the airplane. 

DATES: This AD becomes effective 

January 20, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 20, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0453 or in person at the 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. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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.airwortheas@airbus.com; Internet http://

www.airbus.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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–227–1405; fax: 

425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Airbus Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes. The NPRM published in the 

Federal Register on July 18, 2014 (79 FR 

41940). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0203, 

dated September 6, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Airbus Model A320–211, 

–212, –214, –231, –232, and –233 

airplanes. The MCAI states: 

During the full scale fatigue test on A320– 

200, cracks were reported at the splice plate 

of the frame (FR) 47 butt joint crossing area, 

both sides. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

Prompted by these findings, Airbus 

developed Mod 31012 and introduced this on 

the production line to modify the current 2 

fastener row butt joint into a 3 fastener row 

butt joint to prevent further damage. For inservice aeroplanes, a corresponding 

modification was developed and published 


tkelley on DSK3SPTVN1PROD with RULES
74598 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 

as Airbus Service Bulletin (SB) A320–53– 

1271. 

For the reason described above, this 

[EASA] AD requires repetitive special 

detailed inspections (SDI) of the splice plate 

of the FR47 butt joint crossing area and, 

depending on findings, accomplishment of 

applicable corrective action(s). 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2014-0453-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM (79 FR 41940, 

July 18, 2014) and the FAA’s response. 

Request to Extend the Compliance Time 

Allegiant Air, LLC asked that we 

extend the threshold for the initial 

inspection for the airplanes identified in 

paragraph (g)(3) of the proposed AD (79 

FR 41940, July 18, 2014) to 44,000 flight 

cycles or 88,000 flight hours, whichever 

occurs first. Allegiant Air asserted that 

an equivalent level of safety would be 

maintained by extending the 

compliance time as proposed. Allegiant 

Air noted that paragraph (g)(2) of the 

proposed AD specified a threshold of 

45,000 total flight cycles or 91,000 total 

flight hours, whichever occurs first. 

We do not agree with the commenter’s 

request to extend the compliance time. 

We infer that Allegiant Air, LLC 

expected 44,000 total flight cycles or 

88,000 total flight hours to be the 

threshold for crack growth propagation 

based on full-scale fatigue testing; 

however, Allegiant Air, LLC did not 

provide data to support this inference. 

Based on our risk assessment, taking 

into consideration the worldwide fleet 

utilization, as well as fatigue and crack 

growth analysis, we have determined 

that the compliance time specified in 

paragraph (g)(3) of this AD will ensure 

an acceptable level of safety and allow 

the inspections to be done in a timely 

manner. However, under the provisions 

of paragraph (j) of this AD, we may 

approve requests for adjustments to the 

compliance time if data are submitted to 

substantiate that such an adjustment 

would provide an acceptable level of 

safety. We have not changed this final 

rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this 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 (79 FR 

41940, July 18, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 41940, 

July 18, 2014). 

Costs of Compliance 

We estimate that this AD affects 229 

airplanes of U.S. registry. 

We also estimate that it will take 

about 98 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $1,907,570, or $8,330 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

In addition, we estimate that any 

necessary follow-on actions take about 

100 work-hours and require parts 

costing $1,150, for a cost of $9,650 per 

product. We have no way of 

determining the number of aircraft that 

might 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2014-0453; 

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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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 airworthiness 

directive (AD): 

2014–25–07 Airbus: Amendment 39–18049. 

Docket No. FAA–2014–0453; Directorate 

Identifier 2013–NM–205–AD. 

(a) Effective Date 

This AD becomes effective January 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes, certificated in any category, all 

manufacturer serial numbers, except those on 

which Airbus Modification 31012 has been 

embodied in production. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 74599 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

cracking at the splice plate of the frame (FR) 

47 butt joint crossing area found during fullscale fatigue testing. We are issuing this AD 

to detect and correct fatigue cracking of the 

splice plate of the FR47 butt joint crossing 

area, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Do a special detailed inspection (rototest) for 

cracking of both sides of the splice plate of 

the FR47 butt joint crossing area, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1260, dated December 19, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 14,800 flight cycles or 29,600 flight 

hours, whichever occurs first. 

(1) For airplanes that, as of the effective 

date of this AD, have accumulated 44,000 or 

more total flight cycles or 88,000 or more 

total flight hours since first flight of the 

airplane: Do the inspection within 1,500 

flight cycles or 3,000 flight hours after the 

effective date of this AD, whichever occurs 

first. 

(2) For airplanes that, as of the effective 

date of this AD, have accumulated 27,700 or 

more total flight cycles or 55,400 or more 

total flight hours, but fewer than 44,000 total 

flight cycles or 88,000 total flight hours since 

first flight of the airplane: Do the inspection 

within 3,000 flight cycles or 6,000 flight 

hours after the effective date of this AD, 

without exceeding 45,500 total flight cycles 

or 91,000 total flight hours since first flight 

of the airplane, whichever occurs first. 

(3) For airplanes that, as of the effective 

date of this AD, have accumulated fewer than 

27,700 total flight cycles and less than 55,400 

total flight hours since first flight of the 

airplane: Do the inspection before the 

accumulation of 30,700 total flight cycles or 

61,400 total flight hours since first flight of 

the airplane, whichever occurs first. 

(h) Corrective Action 

If any crack is found during any inspection 

required by this AD: 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 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(i) Optional Modification 

Accomplishing the modification of the 

splice plate of the FR47 butt joint in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1271, dated December 18, 2012, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0203, dated 

September 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2014-0453- 

0002. 

(l) 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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1260, 

dated December 19, 2012. 

(ii) Airbus Service Bulletin A320–53–1271, 

dated December 18, 2012. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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. 

(4) 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. 

(5) 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/ibr-locations.html. 

Issued in Renton, Washington, on 

December 3, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29174 Filed 12–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0257; Directorate 

Identifier 2014–NM–012–AD; Amendment 

39–18051; AD 2014–25–09] 

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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This AD was prompted 

by reports of fatigue cracking in the skin 

assembly and bear strap of the aft lower 

corner of the forward airstair stowage 

doorway. This AD requires repetitive 

inspections for cracking of the skin 

assembly and bear strap of the forward 

airstair stowage doorway; post-repair 

and post-modification inspections for 

certain airplanes; and related 

investigative and corrective actions, if 

necessary. This AD also provides 

optional terminating actions for certain 

inspections. We are issuing this AD to 

detect and correct fatigue cracking, 

which could result in rapid loss of cabin 

pressure. 

DATES: This AD is effective January 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 20, 2015. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://


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