Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 37827 

Dated: June 14, 2012. 

Suzanne Heinen, 

Administrator, Foreign Agricultural Service. 

[FR Doc. 2012–15437 Filed 6–22–12; 8:45 am] 

BILLING CODE 3410–10–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0644; Directorate 

Identifier 2012–NM–011–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Cessna Aircraft Company Model 

750 airplanes. This proposed AD was 

prompted by reports of direct current 

(DC) generator overvoltage events. This 

proposed AD would require replacing 

the auxiliary power unit (APU) 

generator control unit (GCU). We are 

proposing this AD to prevent DC 

generator overvoltage events, which 

could result in subsequent smoke in the 

cockpit and loss of avionics and 

electrical systems. 

DATES: We must receive comments on 

this proposed AD by August 9, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Cessna 

Aircraft Co., P.O. Box 7706, Wichita, 

Kansas 67277; telephone 316–517–6215; 

fax 316–517–5802; email 

citationpubs@cessna.textron.com; 

Internet https:// 

www.cessnasupport.com/newlogin.html. 

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 Management Facility 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Christine Abraham, Aerospace Engineer, 

Electrical Systems and Avionics Branch, 

ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, 

Wichita, Kansas 67209; telephone: 316– 

946–4165; fax: 316–946–4107; email: 

christine.abraham@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0644; Directorate Identifier 2012– 

NM–011–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

We have received reports of direct 

current (DC) generator overvoltage 

events. The GCU overvoltage protection 

circuit can become damaged and allow 

high voltage to pass through to the 

airplane systems and electrical 

components. This condition, if not 

corrected, could result in smoke in the 

cockpit and loss of avionics and 

electrical systems. 

Relevant Service Information 

We reviewed Cessna Service Bulletin 

SB750–24–30, dated December 5, 2011. 

The service information describes 

procedures for replacing the APU GCU 

having part number (P/N) 9914752–2 

with one having P/N 9914752–6. 

Other Relevant Rulemaking 

On January 28, 2011, we issued AD 

2011–03–16, Amendment 39–16600 (76 

FR 8607, February 15, 2011), for Model 

750 airplanes. That AD requires an 

inspection to determine the serial 

numbers of the APU generator and the 

left and right engine DC generators, and 

corrective actions if necessary. That AD 

also requires revising the airplane flight 

manual (AFM). That AD was prompted 

by a report of a DC generator overvoltage 

event, which caused smoke in the 

cockpit and damage to numerous 

avionics and electrical components. In 

that AD, we noted that additional 

rulemaking might be necessary. The 

replacement proposed in this AD is 

necessary in addition to the actions 

required by AD 2011–03–16, in order to 

address the identified unsafe condition. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between the Proposed AD 

and the Service Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

Operators should note that, although 

the Accomplishment Instructions of 

Cessna Service Bulletin SB750–24–30, 

dated December 5, 2011, state that 

operators must return the GCU having 

P/N 9914752–2 to the manufacturer, this 

proposed AD would not include that 

requirement. 

Operators should also note that, 

although the Accomplishment 

Instructions of Cessna Service Bulletin 

SB750–24–30, dated December 5, 2011, 

describe procedures for submitting a 

sheet recording compliance with that 

service bulletin, this proposed AD 

would not include that requirement. 

Costs of Compliance 

We estimate that this proposed AD 

affects 58 airplanes of U.S. registry. 


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37828 Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Replacement ................................................... 2 work-hours × $85 per hour = $170 ............. $2,400 $2,570 $149,060 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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 above, 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, 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. 

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): 

The Cessna Aircraft Company: Docket No. 

FAA–2012–0644; Directorate Identifier 

2012–NM–011–AD. 

(a) Comments Due Date 

We must receive comments by August 9, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Cessna Aircraft 

Company Model 750 airplanes; certificated in 

any category; having serial numbers –0222, 

–0225 through –0306 inclusive, and –0308. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 24, Electrical power. 

(e) Unsafe Condition 

This AD was prompted by reports of direct 

current (DC) generator overvoltage events. 

We are issuing this AD to prevent DC 

generator overvoltage, which could result in 

smoke in the cockpit and loss of avionics and 

electrical systems. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Except as required by paragraph (h) of this 

AD: Within 6 months after the effective date 

of this AD, replace the auxiliary power unit 

generator control unit (GCU) having part 

number (P/N) 9914752–2 with one having 

P/N 9914752–6, in accordance with the 

Accomplishment Instructions of Cessna 

Service Bulletin SB750–24–30, dated 

December 5, 2011. 

(h) Exceptions 

(1) Where the Accomplishment 

Instructions of Cessna Service Bulletin 

SB750–24–30, dated December 5, 2011, state 

that operators must return the GCU having P/ 

N 9914752–2 to the manufacturer, this AD 

does not require that action. 

(2) Where the Accomplishment 

Instructions of Cessna Service Bulletin 

SB750–24–30, dated December 5, 2011, state 

that the operator must record that the service 

bulletin has been completed, this AD does 

not require that action. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) 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. 

(j) Related Information 

(1) For more information about this AD, 

contact Christine Abraham, Aerospace 

Engineer, Electrical Systems and Avionics 

Branch, ACE–119W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

Kansas 67209; telephone: 316–946–4165; fax: 

316–946–4107; email: 

christine.abraham@faa.gov. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Co., P.O. Box 

7706, Wichita, Kansas 67277; telephone 316– 

517–6215; fax 316–517–5802; email 

citationpubs@cessna.textron.com; Internet 

https://www.cessnasupport.com/ 

newlogin.html. 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. 


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Federal Register / Vol. 77, No. 122 / Monday, June 25, 2012 / Proposed Rules 37829 

Issued in Renton, Washington, on June 18, 

2012. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–15451 Filed 6–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0671; Directorate 

Identifier 2011–NM–096–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain Airbus Model 

A330–243, –341, –342 and –343 

airplanes. The existing AD currently 

requires modifying certain cowl 

assemblies of the left- and right-hand 

thrust reversers. Since we issued that 

AD, the manufacturer has issued new 

life limits on certain thrust reverser Cduct assemblies. This proposed AD 

would require removing certain C-duct 

assemblies of the left- and right-hand 

thrust reversers from service at certain 

designated life limits, and would also 

add airplanes to the applicability. We 

are proposing this AD to prevent fatigue 

cracking of the hinges integrated into 

the 12 o’clock beam of the thrust 

reversers, which could result in 

separation of a thrust reverser from the 

airplane, and consequent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 9, 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 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. 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: 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0671; Directorate Identifier 

2011–NM–096–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

On December 2, 2005, we issued AD 

2005–25–21, Amendment 39–14414 (70 

FR 73919, December 14, 2005). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A330–243, –341, –342, and –343 

airplanes equipped with Rolls-Royce 

RB211 TRENT 700 engines. 

Since we issued AD 2005–25–21, 

Amendment 39–14414 (70 FR 73919, 

December 14, 2005), the European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2011–0018, dated February 3, 2011 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI has 

added Model A330–243F airplanes to 

the applicability. The MCAI states: 

The life limits of the thrust reversers Cducts are not addressed by the definition of 

the structural life limits of Safe Life items as 

defined in the A330 Airworthiness 

Limitations Section—ALS Part 1. As a result, 

these life limits are covered by an 

Airworthiness Directive (AD). 

These life limits are due to unexpected 

high fatigue loads (measured during 

certification tests) on the hinges integrated 

into the 12 o’clock beam, which forms the 

upper extreme edge of the thrust reverser CDuct of Rolls Royce Trent 700 engines. 

The aim of the [Direction Ge ́ne ́rale de 

l’Aviation Civile] (DGAC) France AD F– 

2001–528 was to mandate the life limits, 

depending of the modifications applied to 

the C-duct. 

Revision 1 of the DGAC France AD F– 

2001–528 deferred the accomplishment 

threshold of the modification to be applied 

in-service from 6,000 flight cycles (FC) to 

6,500 FC. 

Revision 2 of DGAC France AD F–2001– 

528 [which corresponds to FAA AD 2005– 

25–21, Amendment 39–14414 (70 FR 73919, 

December 14, 2005)] was issued to update 

again the accomplishment threshold from 

6,500 FC to 7,200 FC. 

This [EASA] AD retains the requirements 

of DGAC France AD F–2001–528 R2, which 

is superseded, and adds [certain] life limits. 

The action required in this proposed AD 

is removing certain C-duct assemblies of 

the left- and right-hand thrust reversers 

from service at certain designated life 

limits. This proposed AD also adds 

Model A330–243F airplanes to the 

applicability and revises the 

applicability to include all airplanes of 

the affected models. The unsafe 

condition is fatigue cracking of the 

hinges integrated into the 12 o’clock 

beam of the thrust reversers, which 

could result in separation of a thrust 

reverser from the airplane, and 

consequent reduced controllability 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 A330–78–3010, Revision 03, 

dated April 28, 2004. The actions 


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