Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 71371 

Comments Due Date 

(a) We must receive comments by January 

7, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier, Inc. 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Model DHC–8–102, –103, –106, –201, 

–202, –301, –311, and –315, serial numbers 

003 through 566 inclusive. 

(2) Model DHC–8–401, and –402 airplanes, 

serial numbers 4001, 4003, 4004, 4006, and 

4008 through 4274 inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 56: Windows. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been several in-service reports 

of finding trapped water on the bottom of the 

cockpit windshield frames (or lower 

windshield frames) that resulted in either 

corrosion or water ingress into the cockpit. In 

one occurrence, the trapped water caused 

severe corrosion of numerous anchor nuts 

that secure the windshield to the lower 

windshield frame, such that the intended 

fastening function was seriously 

compromised. Corrosion of the lower 

windshield frames, including the anchor nuts 

that secure the windshield to the aircraft 

structure, can result in a serious structural 

degradation possibly leading to the loss of 

the windshield during flight. Also, water 

could leak into the cockpit and cause either 

a malfunction or failure of the electrical and 

electronics systems in the area of the cockpit 

instrument panels. 

* * * * * 

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 6,000 flight hours or 36 months 

after the effective date of this AD, whichever 

occurs first, install a drain system in the 

cockpit windshield lower frames, and do all 

applicable related investigative and 

corrective actions, in accordance With the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–53–78, Revision C, dated 

April 29, 2010 (for Model DHC–8–102, –103, 

–106, –201, –202, –301, –311, and –315 

airplanes); or 84–53–43, dated April 27, 2010 

(for Model DHC–8–401 and –402 airplanes); 

except where the service bulletins state to 

contact the manufacturer, contact the New 

York Aircraft Certification Office or 

Transport Canada Civil Aviation (TCCA) or 

its delegated agent. Do all applicable related 

investigative and corrective actions before 

further flight. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) For Models DHC–8–102, –103, –106, 

–201, –202, –301, –311, and –315 airplanes: 

Modification of the drain system is also 

acceptable for compliance with the 

requirements of paragraph (g) of this AD, if 

done before the effective date of this AD, in 

accordance with Bombardier Service Bulletin 

8–53–78, dated December 23, 1999; Revision 

A, dated June 7, 2001; or Revision B, dated 

May 2, 2002. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, ANE–170, FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone 516–228–7300; fax 516– 

794–5531. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–16, dated May 18, 2010; 

Bombardier Service Bulletin 8–53–78, 

Revision C, dated April 29, 2010; and 

Bombardier Service Bulletin 84–53–43, dated 

April 27, 2010; for related information. 

Issued in Renton, Washington, on 

November 15, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–29448 Filed 11–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0820; Directorate 

Identifier 2010–NE–31–AD] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Models TAE 

125–01, TAE 125–02–99, and TAE 125– 

02–114 Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Service experience has shown that a case 

of FADEC channel B manifold air pressure 

(MAP) sensor hose permeability is not always 

recognized as fault by the FADEC. The MAP 

value measured by the sensor may be lower 

than the actual pressure value in the engine 

manifold, and limits the amount of fuel 

injected into the combustion chamber and 

thus the available power of the engine. A 

change in FADEC software version 2.91 will 

change the logic in failure detection and in 

switching to channel B (no automatic switch 

to channel B if MAP difference between 

channel A and B is detected and lower MAP 

is at channel B). 

In addition, previous software versions 

allow—under certain conditions and on DA 

42 aircraft only—the initiation of a FADEC 

self test during flight that causes an engine 

in-flight shutdown. 

We are proposing this AD to prevent 

engine in-flight shutdown or power loss, 

possibly resulting in reduced control of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by January 7, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 


erowe on DSK5CLS3C1PROD with PROPOSALS-1
71372 Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696– 

2912; e-mail: info@centurionengines.com for the service information 

identified in this proposed AD. 

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 (phone (800) 647–5527) is the 

same as the Mail address provided 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, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199. 

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–2010–0820; Directorate Identifier 

2010–NE–31–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 with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD 2010–0137, 

dated June 30, 2010 (referred to after 

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

condition for the specified products. 

The MCAI states: 

Service experience has shown that a case 

of FADEC channel B manifold air pressure 

(MAP) sensor hose permeability is not always 

recognized as fault by the FADEC. The MAP 

value measured by the sensor may be lower 

than the actual pressure value in the engine 

manifold, and limits the amount of fuel 

injected into the combustion chamber and 

thus the available power of the engine. A 

change in FADEC software version 2.91 will 

change the logic in failure detection and in 

switching to channel B (no automatic switch 

to channel B if MAP difference between 

channel A and B is detected and lower MAP 

is at channel B). 

In addition, previous software versions 

allow—under certain conditions and on DA 

42 aircraft only—the initiation of a FADEC 

self test during flight that causes an engine 

in-flight shutdown. 

We are proposing to require 

installation of full-authority digital 

electronic control (FADEC) software 

version 2.91 to prevent automatic 

switching to channel B if the channel B 

MAP sensor hose is leaking. The current 

software cannot detect the difference 

between a manifold leak and a real 

manifold pressure change. This software 

installation will prevent the undesired 

limiting of fuel to the engine. Installing 

FADEC software version 2.91 will also 

prevent the FADEC from self-testing 

during flight, which would cause an 

engine in-flight shutdown. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

FAA’s Determination and Requirements 

of This Proposed AD 

These products have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, EASA has 

notified us of the unsafe condition 

described in the MCAI. We are 

proposing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require installing 

full authority digital electronic control 

software version 2.91. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 112 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 0.5 

work-hour per engine to comply with 

this proposed AD. The average labor 

rate is $85 per work-hour. There are no 

required parts cost. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$4,760. 

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 


erowe on DSK5CLS3C1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 71373 

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, 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): 

Thielert Aircraft Engines GmbH: Docket No. 

FAA–2010–0820; Directorate Identifier 

2010–NE–31–AD. 

Comments Due Date 

(a) We must receive comments by January 

7, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH models TAE 125–01, TAE 

125–02–99, and TAE 125–02–114 

reciprocating engines installed in, but not 

limited to, Cessna 172 and (Reims-built) F172 

series (European Aviation Safety Agency 

(EASA) STC No. EASA.A.S.01527); Piper 

PA–28 series (EASA STC No. EASA.A.S. 

01632); APEX (Robin) DR 400 series (EASA 

STC No. A.S.01380); and Diamond Aircraft 

Industries Models DA 40, DA 42, and DA 

42M NG airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent engine in-flight 

shutdown or power loss, possibly resulting in 

reduced control of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, install 

full-authority digital electronic control 

(FADEC) software version 2.91. 

(2) Guidance on FADEC software 

installation can be found in the following: 

(i) For TAE 125–01 engines, Operation & 

Maintenance Manual OM–01–02, Issue 3, 

Revision 13. 

(ii) For TAE 125–02–99 and TAE 125–02– 

114 engines, Operation & Maintenance 

Manual OM–02–02, Issue 1, Revision 10. 

Prohibition of FADEC Software Earlier 

Versions 

(f) Once FADEC software version 2.91 is 

installed, do not install any earlier version of 

FADEC software. 

FAA AD Differences 

(g) EASA AD 2010–0137 permits 

installation of earlier FADEC software 

versions, once version 2.91 is installed. This 

AD does not. 

(h) EASA AD 2010–0137 requires 

compliance within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, but no 

later than 6 months after the effective date of 

the AD. This AD requires compliance within 

110 flight hours after the effective date of the 

AD or during next maintenance, whichever 

occurs first. 

Alternative Methods of Compliance 

(AMOCS) 

(i) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Refer to AD 2010–0137, dated June 30, 

2010, for related information. Contact 

Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, telephone: +49–37204–696–0; fax: 

+49–37204–696–2912; e-mail: 

info@centurion-engines.com, for a copy of 

the service information referenced in this 

AD. 

(k) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; telephone 

(781) 238–7143; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

November 16, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–29449 Filed 11–22–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0494; Directorate 

Identifier 2010–NE–20–AD] 

RIN 2120–AA64 

Airworthiness Directives; International 

Aero Engines V2500–A1, V2522–A5, 

V2524–A5, V2525–D5, V2527–A5, 

V2527E–A5, V2527M–A5, V2528–D5, 

V2530–A5, and V2533–A5 Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

International Aero Engines (IAE) 

V2500–A1, V2522–A5, V2524–A5, 

V2525–D5, V2527–A5, V2527E–A5, 

V2527M–A5, V2528–D5, V2530–A5, 

and V2533–A5 turbofan engines. This 

proposed AD would require initial and 

repetitive 360° borescope inspections of 

high-pressure turbine (HPT) stage 1 

blade outer air seal segments for 

evidence of certain distress conditions. 

This proposed AD would also require 

incorporation of improved durability 

stage 1 blade outer air seal segments at 

the next exposure to the HPT module 

subassembly, as terminating action to 

the repetitive inspections. This 

proposed AD results from three reports 

received of HPT case burn-through 

events, numerous shop reports of loss of 

stage 1 blade outer air seal segments, 

and HPT case bulging. We are proposing 

this AD to prevent HPT case burnthrough, uncontrolled under-cowl 

engine fire, and damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by January 24, 

2011. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 


erowe on DSK5CLS3C1PROD with PROPOSALS-1