Federal Register / Vol. 77, No. 112 / Monday, June 11, 2012 / Proposed Rules 34281 

in multifamily residential housing 

financed by mortgages purchased by 

that Enterprise, and for Freddie Mac, at 

least 32,000 such dwelling units. 

(2) For the year 2013, the subgoal for 

each Enterprise’s purchases of 

mortgages on multifamily residential 

housing affordable to very low-income 

families shall be, for Fannie Mae, at 

least 59,000 dwelling units affordable to 

very low-income families in multifamily 

residential housing financed by 

mortgages purchased by that Enterprise, 

and for Freddie Mac, at least 31,000 

such dwelling units. 

(3) For the year 2014, the subgoal for 

each Enterprise’s purchases of 

mortgages on multifamily residential 

housing affordable to very low-income 

families shall be, for Fannie Mae, at 

least 53,000 dwelling units affordable to 

very low-income families in multifamily 

residential housing financed by 

mortgages purchased by that Enterprise, 

and for Freddie Mac, at least 27,000 

such dwelling units. 

Dated: June 5, 2012. 

Edward J. DeMarco, 

Acting Director, Federal Housing Finance 

Agency. 

[FR Doc. 2012–14105 Filed 6–8–12; 8:45 am] 

BILLING CODE 8070–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0602; Directorate 

Identifier 2009–SW–061–AD] 

RIN 2120–AA64 

Airworthiness Directives; Schweizer 

Aircraft Corporation 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes to 

adopt a new airworthiness directive 

(AD) for Schweizer Aircraft Corporation 

(Schweizer) Model 269D and Model 

269D Configuration A helicopters. The 

type certificate for these models is 

currently held by Sikorsky Aircraft 

Corporation (Sikorsky). This proposal is 

prompted by reports of loose horizontal 

stabilizers and cracks in the stabilizersupport structure for the extruded 

tailboom. The AD would require 

inspecting the aft fuselage assembly in 

the area around the attachment point of 

the horizontal stabilizer, including the 

paint, for a crack. This AD also would 

require inspecting the tailboom interior 

support structure, and if necessary, 

installing an inspection panel kit in the 

aft fuselage assembly, and installing 

doublers in the stabilizer support 

brackets. The actions specified by the 

proposed AD are intended to prevent 

separation of the horizontal stabilizer 

from the helicopter and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 10, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

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 

economic 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 service information identified in 

this proposed AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT 06614; telephone (800) 

562–4409; email 

tsslibrary@sikorsky.com; or at http:// 

www.sikorsky.com. You may review 

copies of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Stephen Kowalski, Aviation Safety 

Engineer, New York Aircraft 

Certification Office, Engine & Propeller 

Directorate, 1600 Stewart Ave. suite 

410, Westbury, NY 11590; telephone 

(516) 228–7327; email 

stephen.kowalski@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

This document proposes adopting a 

new AD for the Schweizer Model 269D 

and Model 269D Configuration A 

helicopters, serial numbers 0001 to 

0062A, with aft fuselage assembly part 

number (P/N) 269D3300–1 installed. 

This proposal is prompted by reports of 

loose horizontal stabilizers and cracks 

in the support structure for the extruded 

tailboom. The actions specified by the 

proposed AD are intended to prevent 

separation of the horizontal stabilizer 

from the helicopter and subsequent loss 

of control of the helicopter. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all known relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Related Service Information 

We have reviewed Schweizer Service 

Bulletin DB–018.3, dated December 13, 

2007 (SB), which specifies inspecting 

for cracks in the fuselage assemblies and 

installing an inspection panel kit and 

stabilizer mount doublers. The Type 

Certificate for these helicopters 

transferred from Schweizer to Sikorsky 

on September 26, 2011. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

34282 Federal Register / Vol. 77, No. 112 / Monday, June 11, 2012 / Proposed Rules 

Proposed AD Requirements 

This proposed AD would require: 

• Before the first flight of each day, 

visually inspecting the aft fuselage 

assembly in the area around the 

attachment point of the horizontal 

stabilizer for a crack. 

• If there is a crack in the aft fuselage 

assembly clip, aft bulkhead, or adjacent 

skins, repairing the crack and either 

performing a repetitive inspection at 

intervals not to exceed 200 hours timein-service (TIS) or replacing the aft 

fuselage assembly. 

• If there is a crack in a longeron, 

tailboom tube collar or a forward 

stabilizer bulkhead, replacing the aft 

fuselage assembly. 

• Within 100 hours TIS or three 

months, whichever occurs first: 

Æ Removing the horizontal stabilizer, 

cleaning the horizontal stabilizer 

mounting brackets, inspecting the 

mounting brackets for wear greater than 

0.002-inch deep, and replacing the 

mounting bracket if the bracket wear 

exceeds 0.002-inch deep. 

Æ Modifying the aft fuselage assembly 

by installing Inspection Panel kit P/N 

SA–269DK–035, installing doublers on 

the forward side of each mounting 

bracket, inspecting the horizontal 

stabilizer forward and aft spars for wear 

in the mounting attachment areas, and 

replacing the spar if the wear exceeds 

0.002-inch deep. 

Æ Inspecting for rivet interference 

between the rivet heads and skin on the 

top surface of the horizontal stabilizer 

and the tailboom stiffening web near 

Station 232.4 and replacing the rivets if 

interference exists. 

Æ Installing an airworthy horizontal 

stabilizer using 4 bolts, P/N NAS1304– 

4, and 4 washers, P/N AN960KD416 or 

NAS1149D0463K. 

• Removing aft fuselage assembly 

P/N 269D3300–1, and replacing it with 

aft fuselage assembly P/N 269D3300–35, 

would be terminating action for the 

requirements of this AD. 

Differences Between This Proposed AD 

and the Service Information 

The Schweizer SB requires contacting 

the manufacturer if certain damage is 

found for repair instructions. This AD 

does not. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 18 helicopters. The average 

labor rate is $85 per work hour. Based 

on these assessments, we estimate the 

following costs: 

• Daily visual inspection. This would 

take about 10 minutes for a labor cost 

of $9. Assuming 365 daily inspections 

per year, the annual labor cost per 

helicopter would be about $3,285. The 

annual cost for the U.S. fleet would total 

$59,130. 

• Internal inspection. This would 

take two work-hours for a labor cost of 

$170. Assuming 10 inspections a year, 

the annual labor cost per helicopter 

would be $1,700. 

• Install inspection panel. This would 

take 16 work-hours for a labor cost of 

$1,360. Parts would cost $150 for a cost 

per helicopter of $1,510. 

• Repair damaged longerons, 

tailboom tube collars, or forward 

stabilizer bulkhead as needed. This 

would take 24 work-hours for a labor 

cost of $2,040. Parts would cost $38,000 

for a cost per helicopter of $40,040. 

• Repair a crack in the aft fuselage 

assembly clip, aft bulkhead, or adjacent 

skins. This would take 24 work-hours 

for a labor cost of $2,040. Parts would 

cost $120 for a cost per helicopter of 

$2,160. 

• Repair interference between the 

rivet heads and skin . This would take 

10 work-hours for a labor cost of $850. 

No parts would be needed. 

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, 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 to the extent that it justifies 

making a regulatory distinction; 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 an economic 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 Airworthiness 

Directive 

(AD): SCHWEIZER AIRCRAFT 

CORPORATION HELICOPTERS: Docket 

No. FAA–2012–0602; Directorate 

Identifier 2009–SW–061–AD. 

(a) Applicability 

This AD applies to Schweizer Aircraft 

Corporation (Schweizer) Model 269D and 

Model 269D Configuration A helicopters, 

serial numbers 0001 to 0062A, with aft 

fuselage assembly part number (P/N) 

269D3300–1 installed, certificated in any 

category. 

Note to Applicability: The type certificate 

for these models is currently held by 

Sikorsky Aircraft Corporation. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loose horizontal stabilizers and cracks in the 

stabilizer support structure for the extruded 

tailboom, which could result in separation of 

the horizontal stabilizer from the helicopter 

and subsequent loss of helicopter control. 

(c) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

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Federal Register / Vol. 77, No. 112 / Monday, June 11, 2012 / Proposed Rules 34283 

(d) Required Actions 

(1) Before the first flight of each day, 

visually inspect the aft fuselage assembly in 

the area around the attachment point of the 

horizontal stabilizer, including the paint, for 

a crack. If there is a crack, remove the 

horizontal stabilizer and perform an interior 

inspection in accordance with Part II: 

Internal Inspection, paragraphs b. and c., of 

Schweizer Service Bulletin DB–018.3, dated 

December 13, 2007 (SB). 

(i) If there is a crack in the aft fuselage 

assembly clip, in the aft bulkhead, or in 

adjacent skins, repair the crack. Thereafter, at 

intervals not to exceed 200 hours time-inservice (TIS), remove the horizontal stabilizer 

and repeat the interior inspection in 

accordance with Part II: Internal Inspection, 

paragraphs b. and c., of the SB, or replace the 

aft fuselage assembly, P/N 269D3300–1,with 

an airworthy aft fuselage assembly, P/N 

269D3300–35. 

(ii) If there is a crack in a longeron, 

tailboom tube collar or a forward stabilizer 

bulkhead, replace the aft fuselage assembly 

with an airworthy aft fuselage assembly, 

P/N 269D3300–35. 

(2) Within 100 hours TIS or three months, 

whichever occurs first: 

(i) Remove the horizontal stabilizer, clean 

the horizontal stabilizer mounting brackets, 

and inspect the mounting brackets for wear 

greater than 0.002-inch deep. If the bracket 

wear exceeds 0.002-inch deep, replace the 

mounting bracket with an airworthy 

mounting bracket. 

(ii) Modify the aft fuselage assembly by 

installing Inspection Panel kit P/N SA– 

269DK–035. 

(iii) Install doublers on the forward side of 

each mounting bracket in accordance with 

Part III–2, paragraphs e. through i., of the SB. 

(iv) Inspect the horizontal stabilizer 

forward and aft spars for wear in the 

mounting attachment areas. If the wear 

exceeds 0.002-inch deep, replace the spar 

with an airworthy spar. 

(v) Inspect for rivet interference between 

the rivet heads and skin on the top surface 

of the horizontal stabilizer and the tailboom 

stiffening web near Station 232.4. If 

interference exists, replace with airworthy 

rivets. 

(vi) Install an airworthy horizontal 

stabilizer using 4 bolts, P/N NAS1304–4, and 

4 washers, P/N AN960KD416 or 

NAS1149D0463K. 

(3) Removing aft fuselage assembly, P/N 

269D3300–1, and replacing it with aft 

fuselage assembly, P/N 269D3300–35, is 

terminating action for the requirements of 

this AD. 

(e) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

provided that before operating the helicopter 

to a location to perform the actions in 

paragraphs (d)(1) through (d)(3) of this AD, 

a daily, pre-flight visual inspection is 

accomplished in accordance with paragraph 

(d)(1) of this AD. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, NYACO, FAA, may 

approve AMOCs for this AD. Send your 

proposal to: Stephen Kowalski, Aviation 

Safety Engineer, New York Aircraft 

Certification Office, Engine & Propeller 

Directorate, 1600 Stewart Ave., suite 410, 

Westbury, NY 11590; telephone (516) 228– 

7327; email stephen.kowalski@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

For service information identified in this 

AD, contact Sikorsky Aircraft Corporation, 

Attn: Manager, Commercial Technical 

Support, mailstop s581a, 6900 Main Street, 

Stratford, CT 06614; telephone (800) 562– 

4409; email tsslibrary@sikorsky.com; or at 

http://www.sikorsky.com. You may review a 

copy of information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302, Rotorcraft tailboom. 

Issued in Fort Worth, Texas, on May 25, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–14037 Filed 6–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1167; Directorate 

Identifier 2011–NM–058–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for certain Airbus Model A319 and 

A320 series airplanes. That NPRM 

proposed to require modification of the 

off-wing escape slide (OWS) enclosures 

on both sides. That NPRM was 

prompted by a report of a torn out 

aspirator due to the aspirator interfering 

with the extrusion lip of the OWS 

enclosure during the initial stage of the 

deployment sequence. This action 

revises that NPRM by adding an 

airplane model to the applicability. We 

are proposing this AD to prevent both 

off-wing exits from being inoperative, 

which, during an emergency, would 

impair the safe evacuation of occupants, 

possibly resulting in personal injuries. 

Since this action imposes an additional 

burden over that proposed in the NPRM, 

we are reopening the comment period to 

allow the public the chance to comment 

on these proposed changes. 

DATES: We must receive comments on 

this proposed AD by July 26, 2012. 

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 service information identified in 

this proposed 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. You 

may review copies of the referenced 

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. 

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: 

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. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS