Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Proposed Rules 65995 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

e-mail me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356. For information on 

the availability of this material at the FAA, 

call 425–227–1221. 

Issued in Renton, Washington, on October 

13, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27484 Filed 10–24–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1091; Directorate 

Identifier 2011–NM–037–AD] 

RIN 2120–AA64 

Airworthiness Directives; EADS CASA 

(Type Certificate Previously Held by 

Construcciones Aeronauticas, S.A.) 

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 

Model CN–235–100, CN–235–200, and 

CN–235–300 airplanes. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

EADS–CASA received reports of engine 

condition control cable * * * failures that, in 

one of the cases, occurred during the starting 

phase of one engine which led to an engine 

shut down following the procedures 

described within the Aircraft Operation 

Manual. 

The investigation revealed that the cable 

failure is due to a fracture in the area of the 

pulley * * *. The root cause of the fracture 

is an unsuitable ratio between the diameter 

of the pulley and the cable type and 

diameter. 

This condition, if not detected and 

corrected, could lead to the engine condition 

control cable failure and consequent runway 

excursion if it occurs during take-off or 

reduced control of the aeroplane if it occurs 

during flight. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by December 9, 2011. 

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 W12–40, 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 EADS–CASA, 

Military Transport Aircraft Division 

(MTAD), Integrated Customer Services 

(ICS), Technical Services, Avenida de 

Arago ́n 404, 28022 Madrid, Spain; 

telephone +34 91 585 55 84; fax +34 91 

585 55 05; e-mail MTA.

TechnicalService@casa.eads.net; 

Internet http://www.eads.net. 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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; 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–2011–1091; Directorate Identifier 

2011–NM–037–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0010, 

dated January 20, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

EADS–CASA received reports of engine 

condition control cable (Part Number (P/N) 

35–56382–0003) failures that, in one of the 

cases, occurred during the starting phase of 

one engine which led to an engine shut down 

following the procedures described within 

the Aircraft Operation Manual. 

The investigation revealed that the cable 

failure is due to a fracture in the area of the 

pulley MS 20219–1. The root cause of the 

fracture is an unsuitable ratio between the 

diameter of the pulley and the cable type and 

diameter. 

This condition, if not detected and 

corrected, could lead to the engine condition 

control cable failure and consequent runway 

excursion if it occurs during take-off or 

reduced control of the aeroplane if it occurs 

during flight. 

To address this condition, EADS–CASA 

has developed an engine condition control 

cable P/N 35–56382–0005 with improved 

characteristics. 

For the reason described above, this 

[EASA] AD requires, at first, [an inspection 

to determine the part number of the engine 

condition control cable] [repetitive detailed] 

inspections for [excessive wear] of the 

[affected] engine condition control cable, and 

its replacement (scheduled or depending of 

the inspection findings) with engine 

condition control cable P/N 35–56382–0005. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Airbus Military has issued Section 

76–10–00, ‘‘Power and Condition 

Control,’’ Block 601 (Configuration 1), 

‘‘Inspection/Check,’’ Paragraph 1.B.; and 

Section 76–10–12, ‘‘Power and Control 

Cables,’’ Block 401 (Configuration 1), 


erowe on DSK2VPTVN1PROD with PROPOSALS
65996 Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Proposed Rules 

‘‘Removal/Installation,’’ Paragraph 3.; of 

the CN–235 Aircraft Maintenance 

Manual, Revision 57, dated July 15, 

2010. The actions described in this 

aircraft maintenance manual are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 7 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$1,190, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 12 work-hours and require parts 

costing $1,087, for a cost of $2,107 per 

product. We have no way of 

determining the number of products 

that may 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 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); and 

3. 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 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 AD: 

EADS CASA (Type Certificate Previously 

Held by Construcciones Aeronauticas, 

S.A.): Docket No. FAA–2011–1091; 

Directorate Identifier 2011–NM–037–AD. 

Comments Due Date 

(a) We must receive comments by 

December 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to EADS CASA (Type 

Certificate previously held by Construcciones 

Aeronauticas, S.A.) Model CN–235–100, CN– 

235–200, and CN–235–300 airplanes; 

certificated in any category; serial numbers 

C–030 through C–149 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 76: Engine controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

EADS–CASA received reports of engine 

condition control cable * * * failures that, in 

one of the cases, occurred during the starting 

phase of one engine which led to an engine 

shut down following the procedures 

described within the Aircraft Operation 

Manual. 

The investigation revealed that the cable 

failure is due to a fracture in the area of the 

pulley * * *. The root cause of the fracture 

is an unsuitable ratio between the diameter 

of the pulley and the cable type and 

diameter. 

This condition, if not detected and 

corrected, could lead to the engine condition 

control cable failure and consequent runway 

excursion if it occurs during take-off or 

reduced control of the aeroplane if it occurs 

during flight. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 9 months or 300 flight hours, 

whichever occurs first after the effective date 

of this AD, inspect to determine whether the 

engine condition control cable has part 

number (P/N) 35–56382–0003. If an engine 

condition control cable having P/N 35– 

56382–0003 is installed, within 9 months or 

300 flight hours, whichever occurs first after 

the effective date of this AD, do a detailed 

inspection for excessive wear of the engine 

condition control cable (including control 

rods, levers and pulleys near the flight 

compartment center console having incorrect 

freedom and range of movement, incorrect 

assembly and locking, distortion, damage, 

corrosion, incorrect security of attachment; 

and control rod end fittings having excessive 

wear, i.e., kinks or distortion, corrosion, 

reduced diameter of cable, and broken wires); 

in accordance with Section 76–10–00, 

‘‘Power and Condition Control,’’ Block 601 


erowe on DSK2VPTVN1PROD with PROPOSALS
Federal Register / Vol. 76, No. 206 / Tuesday, October 25, 2011 / Proposed Rules 65997 

(Configuration 1), ‘‘Inspection/Check,’’ 

Paragraph 1.B., of the Airbus Military CN– 

235 Aircraft Maintenance Manual, Revision 

57, dated July 15, 2010. 

(h) For airplanes with engine condition 

control cable having P/N 35–56382–0003: 

Within 9 months or 300 flight hours after 

doing the detailed inspection required by 

paragraph (g) of this AD, whichever occurs 

first, repeat the detailed inspection specified 

in paragraph (g) of this AD. 

(i) If, during any inspection required by 

paragraph (g) or (h) of this AD, excessive 

wear of the engine condition control cable is 

found: Before further flight, replace the 

engine condition control cable with P/N 35– 

56382–0005, in accordance with Section 76– 

10–12, ‘‘Power and Condition Control 

Cables,’’ Block 401 (Configuration 1), 

‘‘Removal/Installation,’’ Paragraph 3., of the 

Airbus Military CN–235 Aircraft 

Maintenance Manual, Revision 57, dated July 

15, 2010. 

(j) Within 27 months or 900 flight hours, 

whichever occurs first after the effective date 

of this AD: Unless the engine condition 

control cable has already been replaced in 

accordance with paragraph (i) of this AD, 

replace the engine condition control cable 

having P/N 35–56382–0003 with an engine 

condition control cable having P/N 35– 

56382–0005, in accordance with Section 76– 

10–12, ‘‘Power and Condition Control 

Cables,’’ Block 401 (Configuration 1), 

‘‘Removal/Installation,’’ Paragraph 3., of the 

Airbus Military CN–235 Aircraft 

Maintenance Manual, Revision 57, dated July 

15, 2010. 

(k) As of the effective date of this AD, no 

person may install an engine condition 

control cable having P/N 35–56382–0003, on 

any airplane. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences 

Other FAA AD Provisions 

(l) 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: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; fax (425) 

227–1149. Information may be e-mailed 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. 

Related Information 

(m) Refer to MCAI EASA Airworthiness 

Directive 2011–0010, dated January 20, 2011; 

and Section 76–10–00, ‘‘Power and 

Condition Control,’’ Block 601 (Configuration 

1), ‘‘Inspection/Check,’’ Paragraph 1.B., and 

Section 76–10–12, ‘‘Power and Condition 

Control Cables,’’ Block 401 (Configuration 1), 

‘‘Removal/Installation,’’ Paragraph 3., of the 

Airbus Military CN–235 Aircraft 

Maintenance Manual, Revision 57, dated July 

15, 2010; for related information. 

Issued in Renton, Washington, on October 

13, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27485 Filed 10–24–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0994; Directorate 

Identifier 2009–NE–39–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc (RR) RB211–535 Series Turbofan 

Engines 

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 all RR RB211–535E4–37, 

–535E4–B–37, –535E4–B–75, and 

–535E4–C–37 turbofan engines. The 

existing AD currently requires 

performing initial and repetitive visual 

and fluorescent penetrant inspections 

(FPI) of the low-pressure (LP) turbine 

stage 1, 2, and 3 discs to detect cracks 

in the discs. Since we issued that AD, 

we determined that the definition of 

shop visit is too restrictive in the 

existing AD. This proposed AD would 

continue to require those inspections 

and would change the definition of a 

shop visit to be less restrictive. We are 

proposing this AD to correct the 

definition of shop visit, and to detect 

cracks in the LP turbine stage 1, 2, and 

3 discs, which could result in an 

uncontained release of LP turbine 

blades and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by December 27, 

2011. 

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 AD, contact Rolls-Royce plc, P.O. 

Box 31, Derby, DE24 8BJ, United 

Kingdom; phone: 011 44 1332 242424, 

fax: 011 44 1332 249936; or e-mail: 

http://www.rolls-royce.com/contact/ 

civil_team.jsp, or download the 

publication from https:// 

www.aeromanager.com. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

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 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7143; fax: 781– 

238–7199; e-mail: alan.strom@faa.gov. 

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. 


erowe on DSK2VPTVN1PROD with PROPOSALS