This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

72128 

Vol. 76, No. 225 

Tuesday, November 22, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0201; Directorate 

Identifier 2008–NE–47–AD] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise an 

existing airworthiness directive (AD) 

that applies to TAE models TAE 125–01 

and TAE 125–02–99 reciprocating 

engines installed on, but not limited to, 

Diamond Aircraft Industries Model DA 

42 airplanes. The existing AD currently 

requires initial and repetitive 

replacements of proportional pressure 

reducing valves (PPRVs) (also known as 

propeller control valves). Since we 

issued that AD, TAE has increased the 

life of the PPRV, part number (P/N) 05– 

7212–E002801, on TAE 125–02–99 

engines, from 300 hours to 600 hours. 

This proposed AD would relax the 

repetitive replacement interval from a 

300-hour interval to a 600-hour interval 

for PPRVs, P/N 05–7212–E002801, on 

TAE 125–02–99 engines. We are 

proposing this AD to prevent engine inflight shutdown, possibly resulting in 

reduced control of the aircraft. 

DATES: We must receive comments on 

this proposed AD by January 23, 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: 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 Thielert Aircraft 

Engines GmbH, Platanenstrasse 14 D– 

09350, Lichtenstein, Germany; phone: 

+49–37204–696–0; fax: +49–37204– 

696–2912; email: info@centurionengines.com. 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 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, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7143; fax: (781) 238– 

7199; email: 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. 

FAA–2009–0201; Directorate Identifier 

2008–NE–47–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 

On May 19, 2010, we issued AD 

2010–11–09, Amendment 39–16314 (75 

FR 32253, June 8, 2010), for TAE 

Models TAE 125–01 and TAE 125–02– 

99 reciprocating engines installed on, 

but not limited to, Diamond Aircraft 

Industries model DA 42 airplanes. That 

AD requires initial and repetitive 

replacements of PPRVs (also known as 

propeller control valves). That AD 

resulted from reports of in-flight 

shutdown (IFSD) incidents on Diamond 

Aircraft Industries DA 42 aircraft 

equipped with TAE 125 engines. 

Preliminary investigations showed that 

the IFSDs were mainly the result of 

failure of the PPRV. The European 

Aviation Safety Agency issued AD 

2009–0224, dated October 20, 2009, to 

address this unsafe condition in Europe. 

We issued AD 2010–11–09 to prevent 

engine in-flight shutdown, possibly 

resulting in reduced control of the 

aircraft. 

Actions Since Existing AD (75 FR 

32253, June 8, 2010) Was Issued 

Since we issued AD 2010–11–09, TAE 

performed a successful 600-hour 

endurance test of the PPRV, P/N 05– 

7212–E002801, for TAE 125–02–99 

engines only, on a propeller test bench, 

The test also had the vibration isolator 

installed, which was introduced by AD 

2010–11–09. 

Relevant Service Information 

We reviewed TAE Service Bulletin 

(SB) No. TM TAE 125–1007 P1, 

Revision 3, dated October 17, 2011. The 

SB relaxes the PPRV repetitive 

replacement interval from 300 hours to 

600 hours. 

FAA’s Determination 

We are proposing this AD revision, 

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 retain all of 

the requirements of AD 2010–11–09 (75 

FR 32253, June 8, 2010), except the 

repetitive replacement interval in 

paragraph (e)(2). This proposed AD 


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Federal Register / Vol. 76, No. 225 / Tuesday, November 22, 2011 / Proposed Rules 72129 

would relax the repetitive 300-hour 

replacement interval to a 600 hourinterval. 

Costs of Compliance 

We estimate that this AD would affect 

about 300 TAE 125–01 and TAE 125– 

02–99 reciprocating engines installed in 

Diamond Aircraft Industries Model DA 

42 airplanes of U.S. registry. We also 

estimate that it would take about 0.25 

work-hour per engine to replace a PPRV 

and install a vibration isolator to the 

gearbox assembly. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $275 per 

product. Based on these figures, we 

estimate the cost of the AD on U.S. 

operators to be $88,875. 

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 have 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 that the 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 

removing airworthiness directive (AD) 

2010–11–09, Amendment 39–16314 (75 

FR 32253, June 8, 2010), and adding the 

following new AD: 

Thielert Aircraft Engines GmbH: Docket No. 

FAA–2009–0201; Directorate Identifier 

2008–NE–47–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by January 23, 2012. 

(b) Affected ADs 

This AD revises AD 2010–11–09, 

Amendment 39–16314 (75 FR 32253, June 8, 

2010). 

(c) Applicability 

This AD applies to Thielert Aircraft 

Engines GmbH (TAE) models TAE 125–01 

and TAE 125–02–99 reciprocating engines 

designated with part number (P/N) 05–7200– 

K000301 or 02–7200–14017R1. The engines 

are installed on, but not limited to, Diamond 

Aircraft Industries Model DA 42 airplanes. 

(d) Unsafe Condition 

This AD was prompted by engine in-flight 

shutdown incidents reported on Diamond 

Aircraft Industries DA 42 airplanes equipped 

with TAE 125 engines. The investigations 

showed that it was mainly the result of 

failure of the proportional pressure reducing 

valve (PPRV) (also known as the propeller 

control valve) due to high vibrations. Since 

the release of European Aviation Safety 

Agency (EASA) AD 2008–0145, the engine 

gearbox has been identified as the primary 

source of vibrations for the PPRV, and it has 

also been determined that failure of the 

electrical connection to the PPRV could have 

contributed to some power loss events or inflight shutdowns. We are issuing this AD to 

prevent engine in-flight shutdown, possibly 

resulting in reduced control of the aircraft. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) TAE 125–02–99 Reciprocating Engines 

(1) For TAE 125–02–99 reciprocating 

engines with engine, P/N 05–7200–K000301, 

within 55 flight hours after the effective date 

of this AD: 

(i) Replace the existing PPRV with PPRV, 

P/N 05–7212–E002801. Use paragraphs A. 

through B. of TAE Service Bulletin (SB) No. 

TM TAE 125–1007 P1, Revision 3, dated 

October 17, 2011, or SB No. TM TAE 125– 

1007 P1, Revision 2, dated April 29, 2009, to 

do the replacement. 

(ii) Install a vibration isolator, P/N 05– 

7212–K022302, to the gearbox assembly. Use 

paragraphs 1 through 20 of TAE SB No. TM 

TAE 125–1009 P1, Revision 3, dated October 

14, 2009, to do the installation. 

(2) Repetitive PPRV Replacements 

Thereafter, within every 600 flight hours, 

replace the PPRV, P/N 05–7212–E002801, 

with the same P/N PPRV. 

(g) TAE 125–01 Reciprocating Engines 

(1) For TAE 125–01 reciprocating engines 

with engine, P/N 02–7200–14017R1, within 

55 flight hours after the effective date of this 

AD: 

(i) Replace the existing PPRV with a PPRV, 

P/N NM–0000–0124501 or P/N 05–7212– 

K021401. Use paragraph 1 of TAE SB No. TM 

TAE 125–0018, Revision 1, dated November 

12, 2008, to do the replacement. 

(ii) Inspect the electrical connectors of the 

PPRV and replace the connectors if damaged, 

and install a vibration isolator, P/N 05–7212– 

K023801, to the gearbox assembly. Use 

paragraphs 1 through 27 of TAE SB No. TM 

TAE 125–0020, Revision 1, dated November 

25, 2009, to do the inspection and 

installation. 

(3) Repetitive PPRV Replacements 

Thereafter, within every 300 flight hours, 

replace the PPRV with a PPRV, P/N NM– 

0000–0124501 or P/N 05–7212–K021401. 

(h) FAA Differences 

(1) We have found it necessary to not 

reference the second paragraph of the unsafe 

condition from the MCAI EASA AD 2009– 

0224. That sentence stated that the problem 

has only manifested itself on those TAE 

engines installed on Diamond Aircraft 

Industries DA 42 aircraft. The affected 

engines which require a PPRV could be used 

on other make and model airplanes in the 

future. 

(2) We also did not reference the February 

28, 2010 compliance date, which is in EASA 

AD 2009–0193R1, or the January 31, 2010 

compliance date which is in EASA AD 2009– 

0224. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) Refer to EASA AD 2009–0224, dated 

October 20, 2009 (TAE 125–02–99), and 

EASA AD 2009–0193R1, dated December 1, 

2009 (TAE 125–01), for related information. 


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72130 Federal Register / Vol. 76, No. 225 / Tuesday, November 22, 2011 / Proposed Rules 

(2) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

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

238–7199; email: alan.strom@faa.gov, for 

more information about this AD. 

(3) For service information identified in 

this AD, contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, phone: +49–37204– 

696–0; fax: +49–37204–696–2912; email: 

info@centurion-engines.com. 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. 

Issued in Burlington, Massachusetts, on 

November 10, 2011. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30059 Filed 11–21–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–27023; Directorate 

Identifier 98–ANE–47–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney JT9D 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 Pratt & Whitney (PW) 

JT9D series turbofan engines. The 

existing AD currently requires revisions 

to the Airworthiness Limitations 

Section (ALS) of the manufacturer’s 

Instructions for Continued 

Airworthiness (ICA) to include required 

enhanced inspection of selected critical 

life-limited parts at each piece-part 

opportunity. Since we issued that AD, 

PW has added mandatory inspections 

for certain critical life-limited parts. 

This proposed AD would require 

additional revisions to the JT9D series 

engines ALS sections of the 

manufacturer’s ICA. This proposed AD 

results from the need to require 

enhanced inspection of selected critical 

life-limited parts of JT9D series engines. 

We are proposing this AD to prevent 

critical life-limited rotating engine part 

failure, which could result in an 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by January 23, 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. 

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: 

Stephen Sheely, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7750; fax: (781) 238–7199; email: 

stephen.k.sheely@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. 

FAA–2007–27023; Directorate Identifier 

98–ANE–47–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 

On March 1, 2007, we issued AD 

2007–05–17, Amendment 39–14978 (72 

FR 10350, March 8, 2007), for all PW 

JT9D series turbofan engines. That AD 

requires revisions to the ALS of the 

manufacturer’s ICA to include required 

enhanced inspection of selected critical 

life-limited parts at each piece-part 

opportunity. We issued that AD to 

prevent critical life-limited rotating 

engine part failure, which could result 

in an uncontained engine failure and 

damage to the airplane. 

Actions Since Existing AD (72 FR 

10350, March 8, 2007) Was Issued 

Since we issued AD 2007–05–17, an 

FAA study of in-service events 

involving uncontained failures of 

critical rotating engine parts has 

indicated the need for additional 

mandatory inspections. The mandatory 

inspections are needed to identify those 

critical rotating parts with conditions 

which, if allowed to continue in service, 

could result in uncontained engine 

failures. This proposal would require 

revisions to the JT9D series engines ALS 

sections of the manufacturer’s manuals 

and an air carrier’s approved continuous 

airworthiness maintenance program to 

incorporate additional inspection 

requirements. 

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 retain all of 

the requirements of AD 2007–05–17 (72 

FR 10350, March 8, 2007). This 

proposed AD would supersede AD 

2007–05–17 to require the following 

additional inspections: 

• Adding eddy current inspections 

(ECIs) for web cooling holes in highpressure turbine (HPT) stage 1 disks 

installed in engine models JT9D–3A, –7, 

–7A, –7AH, –7F, –7H, –7J, –20, and –20J 

engines; 

• Adding ECIs for web cooling holes 

and tierod holes in HPT stage 2 disks 

installed in JT9D–59A and –70A 

engines; 

• Adding ECIs for web cooling holes 

and tierod holes in HPT stage 2 disks 

installed in JT9D–7Q and –7Q3 engines; 

• Adding ECIs for web cooling holes 

in HPT stage 2 disks, and for fan hub 


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