Federal Register / Vol. 79, No. 107 / Wednesday, June 4, 2014 / Proposed Rules 32197 

6.A. through 6.C. of Turbomeca S.A. MSB 

No. 292 72 2849, Version B, dated November 

25, 2013, to perform the vibration check. The 

reporting requirements in paragraphs 

6.A.(1)(c), 6.A.(2)(b), and 6.B.(1)(c), and the 

requirement to return module M01 in 

paragraph 6.B.(2)(b)2, of Turbomeca S.A. 

MSB No. 292 72 2849, Version B, dated 

November 25, 2013, are not required by this 

AD. 

(2) For all affected Turbomeca S.A. 

engines, during each engine shop visit after 

the effective date of this AD, perform a 

vibration check of the AGB 41/23-tooth bevel 

gear meshing. Guidance on performing the 

vibration check during an engine shop visit 

can be found in the service information listed 

in paragraph (i)(3) in the Related Information 

section. 

(3) If the AGB does not pass the vibration 

check required by paragraphs (e)(1) or (e)(2) 

of this AD, replace the AGB with a part 

eligible for installation. 

(f) Credit for Previous Action 

If you performed a vibration check of the 

AGB before the effective date of this AD 

using Turbomeca S.A. MSB No. 292 72 0839, 

Version A, dated September 9, 2013; or MSB 

No. 292 72 2849, Version A, dated September 

9, 2013, or during an engine shop visit per 

paragraph (e)(2) of this AD, you met the 

initial inspection requirement of paragraph 

(e)(1) of this AD. 

(g) Definition 

For the purposes of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges. The separation of engine flanges 

solely for the purpose of transportation 

without subsequent engine maintenance does 

not constitute an engine shop visit. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs to this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. 

(i) 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; 

phone: (781) 238–7758; fax: (781) 238–7199; 

email: mark.riley@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2014–0036, dated 

February 11, 2014, for related information. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2014–0164. 

(3) Turbomeca S.A. MSB No. 292 72 0839, 

Version B, dated November 25, 2013; and 

MSB No. 292 72 2849, Version B, dated 

November 25, 2013, provide guidance on 

performing the one-time vibration check. 

Arriel 1 Technical Instruction (TI) No. 292 72 

0839, Version E, dated February 20, 2014; 

Arriel 1 TI No. 292 72 0840, dated November 

29, 2013; Arriel 2 TI No. 292 72 2849, 

Version E, dated February 20, 2014; and 

Arriel 2 TI No. 292 72 2850, dated November 

29, 2013, provide detailed instructions on 

performing the one-time vibration check for 

Arriel 1 and Arriel 2 engines, respectively. 

Turbomeca Engine Test Bed Acceptance Test 

Specifications CCT No. 0292009400, Version 

T; CCT No. 0292019400, Version R; CCT No. 

0292019690, Version I; CCT No. 029201530, 

Version K; CCT No. 0292019610, Version K; 

CCT No. 0292029450, Version J; CCT No. 

0292029490, Version I; CCT No. 0292029440, 

Version I; CCT No. 0292029480, Version K; 

CCT No. 0292029520, Version H; CCT No. 

0292029410, Version L; CCT No. 

0292029530, Version H; or Turbomeca ID No. 

383952; or Turbomeca RTD No. X 292 65 327 

2, provide information on performing a 

vibration check during an engine shop visit. 

These service documents can be obtained 

from Turbomeca S.A. using the contact 

information in paragraph (i)(4) of this 

proposed AD. 

(4) For service information identified in 

this proposed AD, contact Turbomeca, S.A., 

40220 Tarnos, France; phone: 33 (0)5 59 74 

40 00; telex: 570 042; fax: 33 (0)5 59 74 45 

15. 

(5) You may view this 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 

May 28, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–12974 Filed 6–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0072; Directorate 

Identifier 2013–NE–04–AD] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2013–15– 

09, which applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, 

PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 turbofan 

engine models with certain second-stage 

high-pressure turbine (HPT) air seals, 

installed. AD 2013–15–09 currently 

requires initial and repetitive 

inspections for cracks in second-stage 

HPT air seals. Since we issued AD 

2013–15–09, we received reports of 

cracking in the original location on two 

additional part numbers (P/Ns) as well 

as reports of through-cracks in a new 

location in the second-stage HPT air 

seal. PW has developed a redesigned 

second-stage HPT air seal that addresses 

the cracking condition in both locations. 

This proposed AD would expand the 

applicability of AD 2013–15–09 to 

include additional P/Ns, require 

replacement of the mating hardware if 

the second-stage HPT air seal is found 

with a through-crack, and add 

mandatory terminating action to the 

repetitive inspections. We are proposing 

this AD to prevent failure of the secondstage HPT air seal, which could lead to 

uncontained engine failure and damage 

to the airplane. 

DATES: We must receive comments on 

this proposed AD by August 4, 2014. 

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 proposed AD, contact Pratt & 

Whitney Division, 400 Main St., East 

Hartford, CT 06108; phone: (860) 565– 

8770; fax: (860) 565–4503. You may 

view this 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 by searching for 

and locating Docket No. FAA–2013– 

0072; 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. 


ehiers on DSK2VPTVN1PROD with PROPOSALS
32198 Federal Register / Vol. 79, No. 107 / Wednesday, June 4, 2014 / Proposed Rules 

FOR FURTHER INFORMATION CONTACT: 

James Gray, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238– 

7199; email: james.e.gray@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–2013–0072; Directorate Identifier 

2013–NE–04–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 July 19, 2013, we issued AD 2013– 

15–09, Amendment 39–17525 (78 FR 

49111, August 13, 2013), (‘‘AD 2013– 

15–09’’), for all PW PW4074, PW4074D, 

PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 turbofan 

engine models with second-stage HPT 

air seal, P/N 54L041, installed. AD 

2013–15–09 requires initial and 

repetitive inspections for cracks in 

second-stage HPT air seals and 

replacement of air seals that fail 

inspection. AD 2013–15–09 resulted 

from the discovery of cracks in secondstage HPT air seals. We issued AD 

2013–15–09 to prevent failure of the 

second-stage HPT air seal, which could 

lead to uncontained engine failure and 

damage to the airplane. 

Actions Since AD 2013–15–09 Was 

Issued 

Since we issued AD 2013–15–09, we 

received multiple reports of throughcracks in a different location on secondstage HPT air seal, P/N 50L041, and 

reports of cracking in the original 

location in two additional second-stage 

HPT air seal P/Ns, 50L960 and 50L976. 

The cracking in the two additional P/Ns 

requires that they be added to the 

applicability of this proposed AD. PW 

has developed a redesigned secondstage HPT air seal that corrects the 

cracking condition in both locations. 

The new cracking location in the 

second-stage HPT air seal, P/N 50L041, 

is in the front forward fillet radius. PW 

determined that through-cracks in the 

front forward fillet radius increase the 

stresses in the mating hardware in the 

HPT rotor and that increased stress 

reduces the life of the first-stage HPT 

hub, second-stage HPT hub, and secondstage HPT blade retaining plate. 

Therefore, the first-stage HPT hub, 

second-stage HPT hub, and second-stage 

HPT blade retaining plate must be 

removed from service if the secondstage HPT air seal, P/N 50L041, is found 

with a through-crack. 

Relevant Service Information 

We reviewed PW Alert Service 

Bulletin (ASB) No. PW4G–112–A72– 

330, Revision 2, dated July 11, 2013, 

which describes procedures for 

inspecting the second-stage HPT air seal 

for cracks and PW Service Bulletin (SB) 

No. PW4G–112–72–332, Revision 2, 

dated April 9, 2014, which describes 

procedures for replacing the secondstage HPT air seal. 

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 expand the 

population of affected P/Ns, require 

removal from service of two newly 

identified P/Ns, require replacement of 

the mating hardware if the second-stage 

HPT air seal is found with a throughcrack, and add mandatory terminating 

action to the repetitive inspection 

requirements. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 116 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 5 

hours to perform the inspection 

required by this proposed AD. The 

average labor rate is $85 per hour. We 

estimate that two engines will also 

require replacement of the first-stage 

HPT hub, second-stage HPT hub, and 

second-stage HPT blade retaining plate. 

We estimate that parts would cost about 

$698,920 per engine. Based on these 

figures, we estimate the total cost of this 

proposed AD to U.S. operators to be 

$23,420,020. 

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 to the extent that it justifies 

making a regulatory distinction, 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. 


ehiers on DSK2VPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 107 / Wednesday, June 4, 2014 / Proposed Rules 32199 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2013–15–09, Amendment 39–17525 (78 

FR 49111, August 13, 2013), and adding 

the following new AD: 

Pratt & Whitney Division: Docket No. FAA– 

2013–0072; Directorate Identifier 2013– 

NE–04–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 4, 2014. 

(b) Affected ADs 

This AD supersedes AD 2013–15–09, 

Amendment 39–17525 (78 FR 49111, August 

13, 2013). 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, PW4077, 

PW4077D, PW4084D, PW4090, and PW4090– 

3 turbofan engine models with second-stage 

high-pressure turbine (HPT) air seal, part 

number (P/N) 54L041, 50L960, or 50L976, 

installed. 

(d) Unsafe Condition 

This AD was prompted by additional 

reports of cracking in the second-stage HPT 

air seal. We are issuing this AD to prevent 

failure of the second-stage HPT air seal, 

which could lead to uncontained engine 

failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next piece-part exposure after the 

effective date of this AD, do the following: 

(i) Remove from service second-stage HPT 

air seals, P/N 50L960, 50L976, and 50L041. 

(ii) Fluorescent-penetrant inspect (FPI) 

second-stage HPT air seal, P/N 50L041, for a 

through-crack in the front forward fillet 

radius. 

(iii) If a through-crack in the front forward 

fillet radius is found, remove the first-stage 

HPT hub, second-stage HPT hub, and secondstage HPT blade retaining plate from service. 

Do not reinstall the first-stage HPT hub, 

second-stage HPT hub, or second-stage HPT 

blade retaining plate into any engine. 

(2) For engines with second-stage HPT air 

seals, P/N 50L041, installed, perform initial 

and repetitive inspections for cracks on-wing 

until the part is removed from the engine as 

follows: 

(i) Perform an initial eddy current 

inspection (ECI) for cracks prior to reaching 

2,200 cycles-since-new or within 100 cyclesin-service after the effective date of this AD, 

whichever occurs later. 

(ii) Thereafter, repeat the ECI every 1,200 

cycles since last inspection, or fewer, 

depending on the results of the inspection. 

(iii) Use section 4.0 of the appendix of PW 

Alert Service Bulletin (ASB) No. PW4G–112– 

A72–330, Revision 2, dated July 11, 2013, to 

perform the inspection and use paragraph 8 

of the Accomplishment Instructions of PW 

ASB No. PW4G–112–A72–330, Revision 2, 

dated July 11, 2013, to disposition the results 

of the inspection. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install any second-stage HPT air seal P/N 

50L041, P/N 50L960, or P/N 50L976 into any 

engine. 

(g) Definitions 

(1) For the purpose of this AD, piece-part 

exposure is when the second-stage HPT air 

seal is removed from the engine and fully 

disassembled. 

(2) For the purpose of this AD, a throughcrack is a crack that has propagated through 

the thickness of the part and can be seen on 

both the inner diameter and outer diameter 

of the front forward fillet radius. 

(h) Credit for Previous Actions 

(1) If you performed an ECI of the secondstage HPT air seal before the effective date of 

this AD, using PW ASB No. PW4G–112– 

A72–330, Revision 1, dated February 14, 

2013, or earlier version, you have met the 

requirements of paragraph (e)(2)(i) of this AD. 

(2) If you performed an in-shop FPI of the 

second-stage HPT air seal before the effective 

date of this AD, you have met the 

requirements of paragraph (e)(2)(i) of this AD. 

(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) For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: (781) 238–7742; fax: (781) 238–7199; 

email: james.e.gray@faa.gov. 

(2) For service information identified in 

this AD, contact Pratt & Whitney Division, 

400 Main St., East Hartford, CT 06108; 

phone: (860) 565–8770; fax: (860) 565–4503. 

(3) You may view this 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 

May 28, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–12973 Filed 6–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Occupational Safety and Health 

Administration 

29 CFR Part 1910 

[Docket Number: OSHA–2007–0073] 

RIN 1218–AC17 

Emergency Response and 

Preparedness 

AGENCY: Occupational Safety and Health 

Administration (OSHA), Labor. 

ACTION: Notice of stakeholder meeting. 

SUMMARY: OSHA invites interested 

parties to participate in an informal 

stakeholder meeting on emergency 

response and preparedness. OSHA 

plans to use the information obtained at 

the stakeholder meeting as it considers 

the development of a proposed standard 

for emergency response and 

preparedness. 

DATES: Date and location for the 

stakeholder meeting are: July 30, 2014, 

at 9:00 a.m., in Washington, DC. If 

needed, a second session will be held 

July 31, 2014. 

The deadline to request registration 

for the meeting is July 2, 2014. 

ADDRESSES: 

I. Registration 

Submit your request to attend the 

stakeholder meeting by one of the 

following methods: 

• Electronic. Register at http://

ersregistration.pec1.net/ (follow the 

instructions online). 

• Facsimile. Fax your request to (240) 

686–3959 and label it ‘‘Attention: OSHA 

Emergency Response and Preparedness 

Stakeholder Meeting Registration.’’ 

• Regular or express mail, hand 

delivery, or messenger (courier) service. 

Send your request, postmarked by July 

2, to: Project Enhancement Corporation, 

20300 Century Blvd. Ste. 175, 

Germantown, MD 20874; Attention: 

OSHA Emergency Response and 

Preparedness Stakeholder Meeting 

Registration. 

II. Stakeholder Meeting 

The stakeholder meeting will be held 

at the Frances Perkins Building, 200 

Constitution Avenue NW., Washington, 

DC, 20210. 

FOR FURTHER INFORMATION CONTACT: 

Information regarding this notice is 

available from the following sources: 

• Press inquiries. Contact Frank 

Meilinger, Director, OSHA Office of 

Communications, Room N–3647, U.S. 

Department of Labor, 200 Constitution 

Avenue NW., Washington, DC, 20210; 


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