16914 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 

3. Vertical (14 G’s) test is to be 

conducted with modified Hybrid II 

ATDs with existing pass/fail criteria. 

Note: It must be demonstrated that the 

installation of seats via plinths or pallets 

meets all applicable requirements. 

Compliance with the guidance contained in 

FAA Policy Memorandum PS–ANM–100– 

2000–00123, dated February 2, 2000, titled 

‘‘Guidance for Demonstrating Compliance 

with Seat Dynamic Testing for Plinths and 

Pallets’’ will be acceptable to the FAA. 

Inflatable Lapbelt Conditions 

If inflatable lapbelts are installed on 

single-place side-facing seats, the 

inflatable lapbelt(s) must meet the final 

inflatable lapbelt special conditions 

(Special Conditions No. 25–431–SC (76 

FR 35324, June 17, 2011). 

Issued in Renton, Washington, on March 

12, 2012. 

John Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service, 

ANM–100. 

[FR Doc. 2012–6957 Filed 3–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0272; Directorate 

Identifier 2011–NM–042–AD; Amendment 

39–16989; AD 2012–06–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A340–211, –212, –311, 

and –312 airplanes. This AD requires 

repetitive inspections for cracking at the 

fastener hole area just above stringer 28, 

of both left- and right-hand fuselage 

frame 39.1, and repair if necessary. This 

AD was prompted by a determination 

that certain airplanes were not included 

in a certain airworthiness limitation 

item (ALI) task (inspections for cracking 

of the fuselage frame 39.1) and that the 

inspections must be done to address the 

identified unsafe condition. We are 

issuing this AD to detect and correct 

cracking in the fuselage that could result 

in reduced structural integrity of the 

airplane. 

DATES: This AD becomes effective April 

9, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 9, 2012. 

We must receive comments on this 

AD by May 7, 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. 

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, 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, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

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 2010–0245, 

dated November 26, 2010 (referred to 

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

unsafe condition for the specified 

products. The MCAI states: 

Airworthiness Limitation Item (ALI) task 

533105–01–01 is applicable to aeroplanes on 

which Airbus modification 40391 has not 

been embodied in production. The 

requirements associated to this task are 

applicable to aeroplanes on which 

Modification Proposal (MP–S10437) has not 

been embodied. 

Following a query from an operator, 

investigations revealed that some MSN 

[manufacturer serial number], for which 

Airbus modification 40391 was indicated as 

fully embodied inside the Aircraft Inspection 

Report (AIR), did not have Modification 

Proposal (MP–S10437) which is part of this 

modification embodied in production. 

As a result, ALI task 533105–01–01 has not 

been taken into account for some MSN listed 

in the applicability section of this AD, which 

constitutes an unsafe condition. 

For the reasons described above, this 

[EASA] AD requires repetitive special 

detailed inspections [for cracking] 

corresponding to ALI task 533105–01–01 and 

the accomplishment of the associated 

corrective actions [repair], for all aeroplanes 

to which this task is applicable. 

Airworthiness Limitation Item (ALI) task 

533105–01–01 will be deleted in the next 

ALS [Airworthiness Limitations Section] Part 

2 revision. 

The unsafe condition is cracking in the 

fuselage that could result in reduced 

structural integrity of the airplane. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A340–53–4184, including 

Appendices 01 and 02, dated October 5, 

2010. 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 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Register 

in the future. 

FAA’s Determination of the Effective 

Date 

Since there are currently no domestic 

operators of this product, notice and 

opportunity for public comment before 

issuing this AD are unnecessary. 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 16915 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0272; 

Directorate Identifier 2011–NM–042– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of 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 AD. 

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. 

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: 

2012–06–08 Airbus: Amendment 39–16989. 

Docket No. FAA–2012–0272; Directorate 

Identifier 2011–NM–042–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 9, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A340– 

211, –212, –311, and –312 airplanes; 

certificated in any category; having 

manufacturer serial numbers (MSN) 0002, 

0003, 0005 through 0009 inclusive, 0011, 

0013, 0014, 0015, 0018 through 0023 

inclusive, 0025, 0026, and 0027. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Reason 

This AD was prompted by a determination 

that certain airplanes were not included in a 

certain airworthiness limitation item (ALI) 

task (inspections for cracking of the fuselage 

frame 39.1) and that the inspections must be 

done to address the identified unsafe 

condition. We are issuing this AD to detect 

and correct cracking in the fuselage that 

could result in reduced structural integrity 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) Inspection 

At the later of the times specified in 

paragraphs (g)(1) or (g)(2) of this AD: Do an 

ultrasonic inspection for cracking at the 

fastener hole area just above stringer 28, of 

both left- and right-hand fuselage frame 39.1, 

in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A340–53–4184, excluding 

Appendices 01 and 02, dated October 5, 

2010. Repeat the inspection thereafter at 

intervals not to exceed 7,850 flight cycles or 

53,300 flight hours, whichever occurs first. 

(1) Before the accumulation of 13,600 total 

flight cycles or 92,100 total flight hours since 

the first flight of the airplane, whichever 

occurs first; or 

(2) Within 6 months after the effective date 

of this AD. 

(h) Repair 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the crack 

using a method approved by Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

initial inspection only, as required by 

paragraph (g) of this AD, if the inspection 

was done before the effective date of this AD 

using Task 533105–01–01, ‘‘Special Detailed 

Inspection of Fuselage Internal Structure, 

Fastener Hole Area Above Stringer 28 at FR 

39.1 Web Junction on Hoist Fitting, LH/RH,’’ 

of Section 2.1, ‘‘A340–200/300 Airworthiness 

Limitations,’’ of the Airworthiness 

Limitations Section (ALS), Part 2 ‘‘DamageTolerant Airworthiness Limitation Items,’’ of 

the Airbus A340 Airworthiness Limitation 

Items (ALI) document 95A.0051/97, Issue 11, 

dated February, 2009. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, 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, Washington 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 


srobinson on DSK4SPTVN1PROD with RULES
16916 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 

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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2010–0245, dated 

November 26, 2010; and Airbus Mandatory 

Service Bulletin A340–53–4184, excluding 

Appendices 01 and 02, dated October 5, 

2010; for related information. 

(l) 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 Mandatory Service Bulletin 

A340–53–4184, dated October 5, 2010. 

(2) For 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. 

(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 March 7, 

2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6778 Filed 3–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1176; Directorate 

Identifier 2011–NE–35–AD; Amendment 39– 

16995; AD 2012–06–14] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney (PW)Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for PW 

JT9D–7R4G2 and –7R4H1 turbofan 

engines. This AD was prompted by the 

determination that a new lower life 

limit for high-pressure turbine (HPT) 1st 

stage air seals, part number (P/N) 

735907, is necessary. This AD 

establishes a new lower life limit for 

HPT 1st stage air seals, P/N 735907, and 

requires removing them from service 

using a drawdown schedule. We are 

issuing this AD to prevent critical lifelimited rotating engine part failure and 

damage to the airplane. 

DATES: This AD is effective April 27, 

2012. 

ADDRESSES: You may review copies of 

the referenced service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document 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 20590. 

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine & 

Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7178; fax: 781– 

238–7199; email: ian.dargin@faa.gov. 

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 published in the Federal 

Register on November 23, 2011 (76 FR 

72348). That NPRM proposed to require 

establishing a new lower life limit for 

HPT 1st stage air seals, P/N 735907, 

from 15,000 cycles-since-new (CSN) to 

9,000 CSN and to require removing 

them from service using a drawdown 

schedule. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM as Written 

The Boeing Company and an 

individual commenter support the 

NPRM (76 FR 72348, November 23, 

2011) as written. 

Request To Revise Applicability 

Commenter PW requested that we 

revise the applicability and summary 

sections of the AD to limit applicability 

to only the PW JT9D–7R4G2 and 

–7R4H1 turbofan engine models. We 

agree. In addition to the JT9D–7R4G2 

and –7R4H1 engines, the NPRM (76 FR 

72348, November 23, 2011) incorrectly 

included JT9D–7R4D, –7R4D1, –7R4E, 

–7R4E1 and –7R4E4 engine models. We 

changed the AD by limiting the 

applicability to only the PW JT9D– 

7R4G2 and –7R4H1 turbofan engine 

models. 

Request To Revise Removal Limits 

Commenter Federal Express requested 

that different removal (drawdown) 

limits be specified for the JT9D–7R4E1 

and –7R4E1H engine models, based on 

the life limits listed in chapter 05 of the 

PW engine manual. 

We do not agree. We removed the 

JT9D–7R4E1 and –7R4E1H engine 

models from this AD in response to 

another comment. Therefore, the JT9D– 

7R4E1 and –7R4E1H engine models are 

no longer affected by this AD. However, 

as these air seals are installed on other 

engine models, we modified the 

installation prohibition paragraph to 

indicate that an air seal removed in 

accordance with this AD cannot be 

installed in any other engine. Further, 

we noted that all air seals identified in 

this AD, when used on the JT9D–7R4E1 

and –7R4E1H engine models, have a 

9,000 CSN life limit. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

Costs of Compliance 

We estimate that this AD will affect 

28 Pratt & Whitney JT9D–7R4G2, and 

–7R4H1 turbofan engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take 28.8 workhours per engine to perform the actions 

required by this AD, and that the 

average labor rate is $85 per work-hour. 


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