Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 9789 

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 

contains the NPRM (77 FR 62182, 

October 12, 2012), 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: 

2013–03–05 Airbus: Amendment 39–17340. 

Docket No. FAA–2012–1070; Directorate 

Identifier 2012–NM–099–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective March 19, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) All Airbus Model A300 B4–601, B4– 

603, B4–620, and B4–622 airplanes; Model 

A300 B4–605R and B4–622R airplanes; 

Model A300 F4–605R and F4–622R 

airplanes; and Model A300 C4–605R Variant 

F airplanes. 

(2) All Airbus Model A310–203, –204, 

–221, –222, –304, –322, –324, and –325 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28; Fuel. 

(e) Reason 

This AD was prompted by fuel system 

reviews conducted by the European Aviation 

Safety Agency (EASA). We are issuing this 

AD to reduce the potential of ignition sources 

inside fuel tanks, which, in combination with 

flammable fuel vapors, could result in fuel 

tank explosions 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) Actions 

Within 48 months after the effective date 

of this AD, accomplish the actions specified 

in paragraph (g)(1) or (g)(2) of this AD, as 

applicable. 

(1) For Model A310 series airplanes: 

Modify the electrical control circuits of the 

inner, center, and trim tank pumps, as 

applicable, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A310–28–2170, 

dated February 28, 2012. 

(2) For Model A300–600 airplanes: Modify 

the electrical control circuits of the inner, 

center, and trim tank pumps, as applicable, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A300–28–6104, dated February 28, 

2012. 

(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, 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; 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 2012–0091, dated May 25, 2012, 

and the service information identified in 

paragraphs (i)(1) and (i)(2) of this AD, for 

related information. 

(1) Airbus Mandatory Service Bulletin 

A310–28–2170, dated February 28, 2012. 

(2) Airbus Mandatory Service Bulletin 

A300–28–6104, dated February 28, 2012. 

(j) 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 the AD specifies otherwise. 

(i) Airbus Mandatory Service Bulletin 

A310–28–2170, dated February 28, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A300–28–6104, dated February 28, 2012. 

(3) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 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. 

(4) You may review copies of the 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/ibrlocations.html. 

Issued in Renton, Washington, on January 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–02723 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0602; Directorate 

Identifier 2009–SW–061–AD; Amendment 

39–17338; AD 2013–03–04] 

RIN 2120–AA64 

Airworthiness Directives; Schweizer 

Aircraft Corporation 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 


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9790 Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 

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 AD 

requires 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 requires 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. This AD is 

prompted by reports of loose horizontal 

stabilizers and cracks in the stabilizer 

support structure for the extruded 

tailboom. The actions are intended to 

prevent separation of the horizontal 

stabilizer from the helicopter and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective March 19, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of March 19, 2013. 

ADDRESSES: 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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 AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

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: 

Discussion 

On June 11, 2012, at 77 FR 34281, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

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. That NPRM 

proposed to require inspecting the aft 

fuselage assembly in the area around the 

attachment point of the horizontal 

stabilizer, including the paint, for a 

crack. That AD also proposed 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 

proposed requirements were prompted 

by reports of loose horizontal stabilizers 

and cracks in the support structure of 

the extruded tailboom. The proposed 

requirements were intended to prevent 

separation of the horizontal stabilizer 

from the helicopter and subsequent loss 

of control of the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(77 FR 34281, June 11, 2012). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

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. 

Differences Between This 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 AD affects 18 

helicopters, and that the average labor 

rate is $85 per work hour. Based on 

these assessments, we estimate the 

following costs: 

• Daily visual inspection. This takes 

about 10 minutes for a labor cost of $9. 

Assuming 365 daily inspections per 

year, the annual labor cost per 

helicopter will be about $3,285. The 

annual cost for the U.S. fleet will total 

$59,130. 

• Internal inspection. This takes two 

work-hours for a labor cost of $170. 

Assuming 10 inspections a year, the 

annual labor cost per helicopter is 

$1,700. 

• Install inspection panel. This takes 

16 work-hours for a labor cost of $1,360. 

Parts cost $150 for a cost per helicopter 

of $1,510. 

• Repair damaged longerons, 

tailboom tube collars, or forward 

stabilizer bulkhead as needed. This 

takes 24 work-hours for a labor cost of 

$2,040. Parts 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 takes 24 work-hours for a 

labor cost of $2,040. Parts cost $120 for 

a cost per helicopter of $2,160. 

• Repair interference between the 

rivet heads and skin. This takes 10 

work-hours for a labor cost of $850. No 

parts are 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 


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Federal Register / Vol. 78, No. 29 / Tuesday, February 12, 2013 / Rules and Regulations 9791 

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 

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 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. 

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): 

2013–03–04 SCHWEIZER AIRCRAFT 

CORPORATION HELICOPTERS: 

Amendment 39–17338; 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) Effective Date 

This AD becomes effective March 19, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has been 

accomplished previously. 

(e) 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. 

(f) Special Flight Permits 

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 (e)(1) through (e)(3) of this AD, a 

daily, pre-flight visual inspection is 

accomplished in accordance with paragraph 

(e)(1) of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, NY ACO, 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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302, Rotorcraft tailboom. 

(i) 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 the AD specifies otherwise. 

(i) Schweizer Service Bulletin DB–018.3, 

dated December 13, 2007. 

(ii) Reserved. 

(3) For Schweizer Aircraft Corporation 

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. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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/ibrlocations.html. 

Issued in Fort Worth, Texas, on January 29, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–02583 Filed 2–11–13; 8:45 am] 

BILLING CODE 4910–13–P 


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