Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 16917 

Required parts will cost about $37,200 

per engine. Based on these figures, we 

estimate the total cost of the AD to U.S. 

operators to be $1,110,144. 

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 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

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): 

2012–06–14 Pratt & Whitney: Amendment 

39–16995; Docket No. FAA–2011–1176; 

Directorate Identifier 2011–NE–35–AD. 

(a) Effective Date 

This AD is effective April 27, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Pratt & Whitney JT9D– 

7R4G2 and –7R4H1 turbofan engines. 

(d) Unsafe Condition 

This AD was prompted by the 

determination that a new lower life limit of 

9,000 cycles-since-new (CSN) for highpressure turbine (HPT) 1st stage air seals, 

part number (P/N) 735907, is necessary. We 

are issuing this AD to prevent critical lifelimited rotating engine part failure, and 

damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Removal of HPT 1st Stage Air Seals, 

P/N 735907 

Remove HPT 1st stage air seals, P/N 

735907, from service as follows: 

(1) For air seals that have fewer than 6,500 

CSN on the effective date of this AD, remove 

the air seals from service before exceeding 

9,000 CSN. 

(2) For air seals that have 6,500 CSN or 

more on the effective date of this AD, do the 

following: 

(i) If the engine has a shop visit before the 

air seal exceeds 9,000 CSN, remove the air 

seal from service before exceeding 9,000 

CSN. 

(ii) If the engine does not have a shop visit 

before the air seal exceeds 9,000 CSN, 

remove the air seal from service at the next 

shop visit, not to exceed 2,500 cycles from 

the effective date of this AD or 15,000 CSN, 

whichever occurs first. 

(g) Installation Prohibition 

(1) After the effective date of this AD, do 

not install or reinstall into any engine any 

HPT 1st stage air seal, P/N 735907, removed 

from service in accordance with paragraph (f) 

of this AD. 

(2) After the effective date of this AD, do 

not install or reinstall into any JT9D–7R4G2 

or JT9D–7R4H1 engine any HPT 1st stage air 

seal, P/N 735907, that exceeds the new life 

limit of 9,000 CSN. 

(h) Engine Shop Visit Definition 

For the purposes of this AD, an engine 

shop visit is the induction of an engine into 

the shop after the effective date of this AD, 

where the separation of a major engine flange 

occurs, except that the following 

maintenance actions, or any combination 

thereof, are not considered engine shop 

visits: 

(1) Introduction of an engine into a shop 

solely for removal of the compressor top or 

bottom case for airfoil maintenance or 

variable stator vane bushing replacement. 

(2) Introduction of an engine into a shop 

solely for removal or replacement of the stage 

1 fan disk. 

(3) Introduction of an engine into a shop 

solely for replacement of the turbine rear 

frame. 

(4) Introduction of an engine into a shop 

solely for replacement of the accessory 

gearbox or transfer gearbox, or both. 

(5) Introduction of an engine into a shop 

solely for replacement of the fan containment 

case. 

(i) 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. 

(j) Related Information 

For more information about this AD, 

contact Ian Dargin, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7178; fax: 781–238– 

7199; email: ian.dargin@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

March 16, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6952 Filed 3–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0288; Directorate 

Identifier 2012–NE–10–AD; Amendment 39– 

16998; AD 2012–06–17] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 


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16918 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 

Rolls-Royce Deutschland (RRD) Models 

Tay 611–8 and Tay 611–8C turbofan 

engines. This AD requires replacement 

of the high-pressure (HP) turbine 

spanner retaining nut. This AD was 

prompted by the discovery that certain 

HP turbine spanner retaining nuts were 

improperly heat treated after application 

of silver plating. We are issuing this AD 

to prevent failure of the HP turbine stage 

2 disc, uncontained engine failure, and 

damage to the airplane. 

DATES: This AD becomes effective 

March 23, 2012. 

We must receive comments on this 

AD by May 7, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: 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. 

For service information identified in 

this AD, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 

7086–1883; fax: 49 0 33–7086–3276. 

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 

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 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: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: mark.riley@faa.gov; phone: 781– 

238–7758; fax: 781–238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Emergency Airworthiness Directive 

2012–0039–E, dated March 9, 2012, and 

EASA AD 2012–0039R1, dated March 

14, 2012 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

A recent quality investigation by RollsRoyce Deutschland has identified that certain 

stage 2 high-pressure turbine (HPT) disc 

spanner retaining nuts did not receive the 

proper heat treatment after application of 

silver plating. This condition, if not 

corrected, could result in a stage 2 HPT disc 

failure, possibly leading to release of high 

energy debris, resulting in damage to the 

aeroplane and/or injury to occupants. 

We are issuing this AD to prevent 

failure of the HP turbine stage 2 disc, 

uncontained engine failure, and damage 

to the airplane. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

RRD has issued Alert Service Bulletin 

No. TAY–72–A1769, dated March 9, 

2012. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

EASA and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with EASA, they 

have notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

issuing 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 

AD requires replacement of the HP 

turbine spanner retaining nut on certain 

serial number engines, within 20 flight 

cycles after the effective date of the AD 

or within 200 flight cycles since the last 

engine shop visit, whichever occurs 

first. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because of the short compliance 

time required to remove the unsafe 

condition. Therefore, we determined 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2012–0288; 

Directorate Identifier 2012–NE–10–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 with FAA 

personnel concerning this 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). 

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 


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Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Rules and Regulations 16919 

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. 

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): 

2012–06–17 Rolls-Royce Deutschland Ltd & 

Co KG (Formerly Rolls-Royce plc, 

Derby, England): Amendment 39–16998; 

Docket No. FAA–2012–0288; Directorate 

Identifier 2012–NE–10–AD. 

(a) Effective Date 

This AD becomes effective March 23, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following RollsRoyce Deutschland Ltd & Co KG (RRD) 

turbofan engines: 

(1) TAY 611–8 engines, serial numbers 

(S/Ns) 16870, 16879, 16880, 16897, 18046, 

18051, 18052, 18053, 18058, 18065, 18066, 

18169, and 18194. 

(2) TAY 611–8C engine S/N 85313. 

(d) Reason 

This AD was prompted by the discovery 

that certain high-pressure (HP) turbine 

spanner retaining nuts were improperly heat 

treated after application of silver plating. We 

are issuing this AD to prevent failure of the 

HP turbine stage 2 disc, uncontained engine 

failure, and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) Within 20 flight cycles after the 

effective date of the AD or within 200 flight 

cycles since the last engine shop visit, 

whichever occurs first, remove the HP 

turbine spanner retaining nut from the 

combustion and HP turbine module, and 

install a new HP turbine spanner retaining 

nut. 

(2) Do not reinstall HP turbine spanner 

retaining nuts removed as specified in 

paragraph (e)(1) of this AD, into any engine. 

(f) 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. 

(g) Related Information 

(1) For more information about this AD, 

contact Mark Riley, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

email: mark.riley@faa.gov; phone: 781–238– 

7758; fax: 781–238–7199. 

(2) Refer to MCAI European Aviation 

Safety Agency Emergency AD 2012–0039–E, 

dated March 9, 2012; AD 2012–0039R1, 

dated March 14, 2012; and RRD Alert Service 

Bulletin No. TAY–72–A1769, dated March 9, 

2012, for related information. 

(3) For service information identified in 

this AD, contact Rolls-Royce Deutschland Ltd 

& Co KG, Eschenweg 11, Dahlewitz, 15827 

Blankenfelde-Mahlow, Germany; phone: 49 0 

33–7086–1883; fax: 49 0 33–7086–3276. 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 

March 19, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6995 Filed 3–22–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1090; Directorate 

Identifier 2011–NM–138–AD; Amendment 

39–16986; AD 2012–06–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model DHC–8–400 

series airplanes. This AD was prompted 

by a report of the inability to open the 

airstair door while on the ground, 

because the airstair door seal did not 

deflate, which prevented the airstair 

door from opening. This AD requires 

changing the wiring that controls the 

pneumatic shut-off valve. We are 

issuing this AD to prevent the airstair 

door seal from not deflating, which 

could result in the airstair door not 

opening and could impede evacuation 

in the event of an emergency. 

DATES: This AD becomes effective April 

27, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 27, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

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 October 19, 2011 (76 FR 

64847). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 


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