Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 13485 

the procedures found in 14 CFR 39.19 to 

make your request. 

(j) Related Information 

(1) For more information about this AD, 

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. 

(2) See European Aviation Safety Agency 

Airworthiness Directive 2009–0073R1, dated 

April 8, 2009, for related information. 

(k) 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) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(i) Rolls-Royce Alert Service Bulletin No. 

RB.211–72–AF964, Revision 2, dated June 8, 

2011 approved for IBR April 11, 2012. 

(ii) Rolls-Royce ASB No. RB.211–72– 

AF964, Revision 1, dated June 6, 2008 

approved for IBR June 7, 2011 (76 FR 24793, 

May 3, 2011). 

(2) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–245418 or email 

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

civil_team.jsp, or download the publication 

from https://www.aeromanager.com. 

(3) You may review copies of the 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. 

(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 NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Burlington, Massachusetts, on 

February 23, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5370 Filed 3–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0959; Directorate 

Identifier 2011–NE–25–AD; Amendment 39– 

16970; AD 2012–04–14] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for RB211– 

Trent 800 series turbofan engines. This 

AD requires inspecting the front 

combustion liner head section for 

cracking, and if found cracked, 

removing the front combustion liner 

head section from service at the next 

shop visit. This AD was prompted by 

mandatory continuing airworthiness 

information (MCAI) issued by an 

aviation authority of another country to 

identify and correct an unsafe condition 

on an aviation product. Specifically, 

routine inspections revealed cracking on 

the head sections of two RB211–Trent 

800 front combustion liners. We are 

issuing this AD to prevent uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD becomes effective April 

11, 2012. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in this AD as of April 11, 2012. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: alan.strom@faa.gov; phone: 781– 

238–7143; fax: 781–238–7199. 

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 was published in the Federal 

Register on November 25, 2011 (76 FR 

72650). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Routine inspections have revealed cracking 

on the head sections of two Trent 800 front 

combustion liners. 

This condition, if not detected and 

corrected, could lead to hot gas breakout with 

subsequent downstream component release 

potentially leading to uncontained high 

energy debris, possibly resulting in damage 

to the aeroplane or injury to persons on the 

ground. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Reference the Latest Service 

Information 

American Airlines, The Boeing 

Company, and Rolls-Royce plc, 

requested that we reference the latest 

service information, which is Alert 

Service Bulletin (ASB) No. RB.211–72– 

AG456, Revision 1, dated November 4, 

2011. 

We agree. We changed the AD to 

reference Revision 1 of the ASB. 

Request To Add Previous Credit 

Paragraph 

American Airlines, The Boeing 

Company, and Rolls-Royce plc, 

requested that we add a Previous Credit 

paragraph to list the original ASB to 

give credit to operators who have 

performed the initial and repetitive 

inspections before the effective date of 

the AD. 

We agree. We added Credit for 

Previous Action paragraph (i) to the AD. 

Request To Borescope-Inspect the 04 

Module When Removed 

Rolls-Royce plc requested that we add 

wording to the AD that states that the 04 

module may be borescope-inspected 

when it is removed from the engine but 

is not being stripped. This would give 

the operator the opportunity to restart 

the 2,000-cycle on-wing life before the 

next inspection, or if cracked, would 

give the operator the opportunity to 

replace the front combustion liner head 

section. 

We agree. We changed the AD to 

allow as an alternate procedure, an inshop borescope inspection. 

Request To Eliminate Unnecessary 

Borescope Inspection 

Rolls-Royce plc pointed out that the 

proposed AD requires the front 

combustion liner head section to be 

borescope inspected even if it is being 

stripped. Visual and fluorescent 

penetrant inspections would be done as 

part of the maintenance manual 

activities after stripping, and the 

borescope inspection would be 

unnecessary. 


srobinson on DSK4SPTVN1PROD with RULES
13486 Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 

We agree. We changed the AD to 

eliminate the unnecessary borescope 

inspection. 

Request To Clarify AD Meaning 

American Airlines and The Boeing 

Company requested that we change 

paragraphs (f)(2) and (g)(1)(i) to state 

that if you find cracking, repetitively 

inspect the front combustion liner as 

specified in Table 1 and remove it from 

service as specified in Table 1 or at the 

next shop visit, whichever occurs first. 

The commenters claim that this change 

would clarify the meaning of the AD. 

We do not agree. Any engine found to 

have cracks during the initial inspection 

in paragraph (f)(1) or a repetitive 

inspection in paragraph (g)(1) must have 

its front combustor liner head section 

removed from service at the next shop 

visit. Table 1 allows for further flight 

with mitigating actions until the next 

shop visit. We did not change the AD. 

Request To Identify the Repetitive 

Inspections Paragraph 

The Boeing Company requested that 

we identify the repetitive inspections 

paragraph, as paragraph (g). 

We do not agree. The paragraph is 

already identified as paragraph (g). We 

did not change the AD. 

Request To Remove Erroneous 

Reference 

American Airlines requested that in 

paragraph (g)(2), we not reference 

paragraph (f)(2) as being a step that 

would find cracks, because it does not. 

We agree. We removed that reference 

in the AD. 

Request To Revise Shop Visit Definition 

and To Inspect During All Shop Visits 

American Airlines requested that we 

revise the definition of shop visit to 

include all engine shop visits, and 

revise paragraph (g)(2) of the proposed 

AD such that paragraph 3.B.(1) or 3.B.(2) 

of the ASB can be used to do the 

inspections. The commenter stated that 

the proposed AD shop visit definition 

limits the number of shop visits where 

an inspection is required. Further, 

paragraph (g)(2) of the proposed AD is 

inconsistent with the definition of shop 

visit in the ASB because the ASB has 

instructions for borescope inspection 

when the front combustor liner head 

section is not exposed. 

We partially agree. We agree with 

revising paragraph (g)(2) (now 

paragraph (g)(3) in the AD) and 

paragraph (h), because Revision 1 of the 

ASB is worded differently from the 

original ASB, and Revision 1 of the ASB 

added an alternate borescope inspection 

that can be performed without 

disassembling the 04 module. 

We do not agree with requiring the 

inspection during all shop visits 

because the mitigating actions in Table 

1 of the AD are sufficient to ensure safe 

operation pending a shop visit in 

accordance with the definition of shop 

visit in the AD. We changed paragraph 

(g)(2) (now paragraph (g)(3)) from: 

‘‘For engines not found to have cracks 

in the front combustion liner head 

section in accordance with paragraphs 

(f)(1), (f)(2), or (g)(1) of this AD, at every 

shop visit after the effective date of this 

AD, inspect the front combustion liner 

head section for cracking. Use paragraph 

B.(2), except B.(2)(a)(i), of the In-shop 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG456, dated 

September 9, 2010, to do the 

inspections,’’ to: 

‘‘For engines not found to have cracks 

in the front combustion liner head 

section in accordance with paragraphs 

(f)(1) or (g)(1) of this AD, at every shop 

visit after the effective date of this AD: 

(i) Fluorescent-penetrant inspect the 

front combustion liner head section for 

cracking; or 

(ii) Borescope-inspect the front 

combustion liner head section for 

cracking. Use paragraph 3.B.(1)(b) 

except paragraph 3.B.(1)(b)(i), or use 

paragraphs 3.B.(2)(b) through 3.B.(2)(d), 

of the In-shop Accomplishment 

Instructions of RR ASB No. RB.211–72– 

AG456, Revision 1, dated November 4, 

2011. 

(iii) If any cracks are found, reject the 

front combustion liner.’’ 

We also changed paragraph (h) from: 

‘‘For the purpose of this AD, the term 

shop visit means the induction of an 

engine into the shop for maintenance 

where the front combustion liner is 

exposed or when the engine has been 

removed from service as a result of 

paragraph (f)(2) or (g)(1)(i) of this AD,’’ 

to: 

‘‘For the purpose of this AD, the term 

shop visit means the induction of an 

engine into the shop for maintenance 

where the front combustion liner is 

exposed, or when the 04 module has 

been removed from the engine or when 

the engine has been removed from 

service as a result of paragraph (f)(2) or 

(g)(2) of this AD.’’ 

Request To Change Action Wording in 

Table 1 

The Boeing Company requested that 

we change the action wording in Table 

1 of the proposed AD from ‘‘Replace the 

engine before next flight’’ to ‘‘Remove 

the engine immediately.’’ The 

commenter stated that this would make 

the AD consistent with the ASB and 

prevent failures on the ground. 

We do not agree. Engine running on 

the ground is not a flight safety issue. 

We note, however, that the NPRM (76 

FR 72650, November 25, 2011) used 

both ‘‘remove the engine’’ and ‘‘replace 

the engine’’ in Table 1. We changed 

Table 1 in the AD to use the phrase, 

‘‘remove the engine’’ in each case. 

Need To Show All Acceptable Means of 

Completing the On-Wing Inspection 

Since we issued the NPRM (76 FR 

72650, November 25, 2011), we 

determined that to be consistent with 

Revision 1 of the ASB, we need to show 

all acceptable means of completing the 

on-wing inspection. We changed 

paragraphs (f)(1) and (g)(1) of the 

proposed AD from: 

‘‘Within 1,000 flight cycles (FCs) after 

the effective date of this AD, inspect the 

front combustion liner head section for 

cracking. Use paragraph 3.A, except for 

3.A.(1)(a)(i), of the On-Wing 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG456, dated 

September 9, 2010, to do your 

inspections’’ to: 

‘‘Within 1,000 flight cycles (FCs) after 

the effective date of this AD, inspect the 

front combustion liner head section for 

cracking. Use paragraph 3.A.(1), except 

for 3.A.(1)(a)(i), or paragraphs 3.A.(2)(b) 

through 3.A.(2)(d) of the On-Wing 

Accomplishment Instructions of RR 

ASB No. RB.211–72–AG456, Revision 1, 

dated November 4, 2011, to do your 

inspections.’’ 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 125 products of U.S. registry. We 

also estimate that it will take about 10 

work-hours per engine to inspect and 10 

additional work-hours for those 

combustion liners that require 

replacement. The average labor rate is 

$85 per work-hour. Required parts will 

cost about $525,000 per engine. We 

expect that four front combustion liners 

will require replacement. Based on 

these figures, we estimate the cost of the 

AD on U.S. operators to be $2,209,650. 


srobinson on DSK4SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 13487 

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 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); 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 AD and placed it in the AD docket. 

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 (phone: 

800–647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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 airworthiness 

directive (AD): 

2012–04–14 Rolls-Royce plc: Amendment 

39–16970; Docket No. FAA–2011–0959; 

Directorate Identifier 2011–NE–25–AD. 

(a) Effective Date 

This AD becomes effective April 11, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Rolls-Royce plc (RR) 

RB211–Trent 800 turbofan engines, all 

models, all serial numbers. 

(d) Reason 

(1) 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. The MCAI 

describes the unsafe condition as: 

Routine inspections have revealed cracking 

on the head sections of two Trent 800 front 

combustion liners. 

This condition, if not detected and 

corrected, could lead to hot gas breakout with 

subsequent downstream component release 

potentially leading to uncontained high 

energy debris, possibly resulting in damage 

to the aeroplane or injury to persons on the 

ground. 

(2) We are issuing this AD to prevent 

uncontained engine failure and damage to 

the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) Initial Inspection 

(1) Within 1,000 flight cycles (FCs) after 

the effective date of this AD, inspect the front 

combustion liner head section for cracking. 

Use paragraph 3.A.(1), except for 3.A.(1)(a)(i), 

or paragraphs 3.A.(2)(b) through 3.A.(2)(d) of 

the On-Wing Accomplishment Instructions of 

RR Alert Service Bulletin (ASB) No. RB.211– 

72–AG456, Revision 1, dated November 4, 

2011, to do your inspections. 

(2) If you find cracking, remove the front 

combustion liner head section from service at 

the next shop visit. Until the next shop visit, 

take the corrective actions listed in Table 1 

of this AD, as applicable. 

TABLE 1—INSPECTION FINDINGS AND FOLLOW-ON ACTIONS

Inspection findings Action(s) and compliance time(s) 

(i) Cumulative crack length up to 150 mm (up to 2 heatshields) ........................................................ Reduce the inspection intervals to 250 FCs. 

(ii) Cumulative crack length 150 mm to 300 mm (up to 4 heatshields) .............................................. Reduce the inspection intervals to 100 FCs. 

(iii) Cumulative crack length 300 mm to 450 mm (up to 6 heatshields) ............................................. Remove the engine within 50 FCs. 

(iv) Cumulative crack length 450 mm to 900 mm (up to 12 heatshields) ........................................... Remove the engine within 5 FCs. 

(v) Cumulative crack length greater than 900 mm (more than 12 heatshields) ................................. Remove the engine before next flight. 

(g) Repetitive Inspections 

(1) Within 1,000 FCs after the effective date 

of this AD, inspect the front combustion liner 

head section for cracking. Use paragraph 

3.A.(1), except for 3.A.(1)(a)(i), or paragraphs 

3.A.(2)(b) through 3.A.(2)(d) of the On-Wing 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AG456, Revision 1, dated 

November 4, 2011, to do your inspections. 

(2) If you find cracking, remove the front 

combustion liner head section at the next 

shop visit. Until the next shop visit, take the 

corrective actions as detailed in Table 1 of 

this AD, as applicable. 

(3) For engines not found to have cracks in 

the front combustion liner head section in 

accordance with paragraphs (f)(1) or (g)(1) of 

this AD, at every shop visit after the effective 

date of this AD: 

(i) Fluorescent-penetrant inspect the front 

combustion liner head section for cracking; 

or 

(ii) Borescope-inspect the front combustion 

liner head section for cracking. Use 

paragraph 3.B.(1)(b) except paragraph 

3.B.(1)(b)(i), or use paragraphs 3.B.(2)(b) 

through 3.B.(2)(d), of the In-shop 

Accomplishment Instructions of RR ASB No. 

RB.211–72–AG456, Revision 1, dated 

November 4, 2011. 

(iii) If any cracks are found, reject the front 

combustion liner. 

(4) Accomplishment of a shop visit 

inspection as required by paragraph (g)(3) of 

this AD may substitute for the 

accomplishment of an on-wing inspection as 


srobinson on DSK4SPTVN1PROD with RULES
13488 Federal Register / Vol. 77, No. 45 / Wednesday, March 7, 2012 / Rules and Regulations 

required by paragraph (f)(1) or (g)(1) of this 

AD. 

(h) Definition of Shop Visit 

For the purpose of this AD, the term shop 

visit means the induction of an engine into 

the shop for maintenance where the front 

combustion liner is exposed, or when the 04 

module has been removed from the engine, 

or when the engine has been removed from 

service as a result of paragraph (f)(2) or (g)(2) 

of this AD. 

(i) Credit for Previous Action 

An initial or repetitive inspection 

performed before the effective date of this AD 

using RR ASB No. RB.211–72–AG456, dated 

September 9, 2010, satisfies the initial 

inspection requirement in paragraph (f) or 

repetitive inspection requirement in 

paragraph (g) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(k) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: alan.strom@faa.gov; phone: 781–238– 

7143; fax: 781–238–7199. 

(2) Refer to European Aviation Safety 

Agency AD 2011–0080, dated May 6, 2011, 

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) under 5 

U.S.C. 552(a) and 1 CFR part 51. 

(i) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–72–AG456, Revision 1, dated 

November 4, 2011. 

(ii) Rolls-Royce plc Alert Service Bulletin 

No. RB.211–72–AG456, dated September 9, 

2010. 

(2) 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; email: http://www.rolls-royce.com/ 

contact/civil_team.jsp; or Web: https:// 

www.aeromanager.com. 

(3) You may review copies of the 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. 

(4) You may also review copies of the 

service information incorporated by reference 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

February 22, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5371 Filed 3–6–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0201; Directorate 

Identifier 2008–NE–47–AD; Amendment 39– 

16972; AD 2010–11–09R1] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH (TAE) 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) 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 currently requires initial and 

repetitive replacements of proportional 

pressure reducing valves (PPRVs) (also 

known as propeller control valves). This 

new AD relaxes 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 engine. This AD was 

prompted by TAE increasing the life of 

the PPRV, part number (P/N) 05–7212– 

E002801, on TAE 125–02–99 engines 

from 300 to 600 hours. We are issuing 

this AD to prevent engine in-flight 

shutdown, possibly resulting in reduced 

control of the aircraft. 

DATES: This AD is effective April 11, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of April 11, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 13, 2010 (75 FR 

32253, June 8, 2010). 

ADDRESSES: 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. 

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: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2010–11–09, 

Amendment 39–16314 (75 FR 32253, 

June 8, 2010). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

November 22, 2011 (76 FR 72128). That 

NPRM proposed to retain all of the 

requirements of AD 2010–11–09, except 

the repetitive replacement interval in 

paragraph (e)(2). This AD relaxes the 

repetitive 300-hour replacement interval 

to a 600-hour interval. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 72128, November 22, 2011). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 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 will take 0.25 work-hour 

per engine to replace a PPRV and install 

a vibration isolator to the gearbox 


srobinson on DSK4SPTVN1PROD with RULES