16968 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules 

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), 

(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 adding 

the following new airworthiness 

directive (AD): 

Pratt & Whitney Division: Docket No. FAA– 

2012–0079; Directorate Identifier 2012– 

NE–06–AD. 

(a) Comments Due Date 

We must receive comments by May 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following Pratt & 

Whitney Division turbofan engines: 

(1) PW4052, PW4152, and PW4056 

turbofan engines, including models with any 

dash number suffix, with the following highpressure turbine (HPT) stage 1 front hub part 

numbers (P/Ns) installed: 

(i) P/N 51L201, or P/N 51L201–001, or 

P/N 51L601, or P/N 52L401; or 

(ii) P/N 51L901 with a serial number (S/N) 

not listed in Table 9 of the Accomplishment 

Instructions of Pratt & Whitney Service 

Bulletin (SB) No. PW4ENG 72–795, Revision 

2, dated April 5, 2011. 

(2) PW4156A, PW4060, PW4060A, 

PW4060C, PW4062, PW4062A, PW4158, 

PW4460, and PW4462 turbofan engines, 

including models with any dash number 

suffix, with the following HPT stage 1 front 

hub P/Ns installed: 

(i) P/N 51L201, or P/N 51L201–001, or 

P/N 52L401; or 

(ii) P/N 51L901 with an S/N not listed in 

Table 9 of the Accomplishment Instructions 

of Pratt & Whitney SB No. PW4ENG 72–795, 

Revision 2, dated April 5, 2011. 

(3) PW4164, PW4164C, PW4164C/B, 

PW4168, and PW4168A turbofan engines 

with an HPT stage 1 front hub P/N 51L901 

installed with a S/N not listed in Table 27A 

of the Accomplishment Instructions of Pratt 

& Whitney SB No. PW4G–100–72–220, 

Revision 4, dated September 30, 2011. 

(d) Unsafe Condition 

This AD was prompted by Pratt & 

Whitney’s updated low-cycle-fatigue analysis 

that indicated certain HPT stage 1 front hubs 

could initiate a crack prior to the published 

life limit. This AD requires removing the 

affected HPT stage 1 front hubs from service 

using a drawdown plan. We are issuing this 

AD to prevent failure of the HPT stage 1 front 

hub, which could lead to an uncontained 

engine failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) Removal of HPT Stage 1 Front Hubs From 

Service 

(1) For HPT stage 1 front hubs listed in 

paragraph (c)(1)(i) and (c)(1)(ii) of this AD, do 

the following: 

(i) If the HPT stage 1 front hub has 

accumulated 17,000 or fewer cycles-since 

new (CSN) on the effective date of this AD, 

remove the HPT stage 1 front hub from 

service before accumulating 18,000 CSN. 

(ii) If the HPT stage 1 front hub has 

accumulated more than 17,000 CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating an additional 1,000 cycles-inservice (CIS), or at the next piece-part 

exposure after the effective date of this AD, 

whichever occurs first. 

(2) For HPT stage 1 front hubs listed in 

paragraphs (c)(2)(i), (c)(2)(ii), and (c)(3) of 

this AD, do the following: 

(i) If the HPT stage 1 front hub has 

accumulated 12,700 or fewer CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating 13,700 CSN. 

(ii) If the HPT stage 1 front hub has 

accumulated more than 12,700 CSN on the 

effective date of this AD, remove the HPT 

stage 1 front hub from service before 

accumulating an additional 1,000 CIS, or at 

the next piece-part exposure after the 

effective date of this AD, whichever occurs 

first. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install or reinstall into any engine any HPT 

stage 1 front hubs listed in paragraph (c)(1)(i) 

and (c)(1)(ii) of this AD that are at piece-part 

exposure and exceed 18,000 CSN, or any 

HPT stage 1 front hubs listed in (c)(2)(i), 

(c)(2)(ii), and (c)(3) of this AD that are at 

piece-part exposure and exceed 13,700 CSN. 

(h) Definition 

For the purpose of this AD, piece-part 

exposure means that the part is completely 

disassembled and removed from the engine. 

(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 

(1) For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA; 

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, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–7700; fax: 860–565–1605. 

(3) 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 14, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–6965 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–2012–0324; Directorate 

Identifier 2012–CE–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; Burkhart 

GROB Luft- und Raumfahrt GmbH 

Powered Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules 16969 

Burkhart GROB Luft- und Raumfahrt 

GmbH Models GROB G 109 and GROB 

G 109B powered sailplanes. This 

proposed AD results from mandatory 

continuing airworthiness information 

(MCAI) originated 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 excessive 

corrosion on the nose plate in the 

vertical stabilizer, which could cause 

the vertical stabilizer nose plate to fail. 

We are issuing this proposed AD to 

require actions to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed 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. 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Grob Aircraft 

AG, Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Germany; 

telephone: +49 (0) 8268 998139; fax: +49 

(0) 8268 998200; email: 

productsupport@grob-aircraft.com; 

Internet: http://www.grobaircraft.de.61.html. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Jim 

Rutherford, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 

329–4090; email: 

jim.rutherford@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–2012–0324; Directorate Identifier 

2012–CE–008–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:// 

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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No. 2012– 

0027, dated February 14, 2012 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Occurrences have been reported of finding 

heavily corroded nose plates, part number (P/ 

N) 109–2160.01, in the vertical stabiliser of 

some Grob G 109 powered sailplanes. 

The investigation results concluded that 

the affected aeroplanes were based and 

operated near the seaside and therefore 

exposed to a salty environment, causing the 

excessive corrosion. 

This condition, if not detected and 

corrected, could lead to failure of the vertical 

stabilizer nose plate, which functions as a 

horizontal stabiliser fitting, to support limit 

loads and consequent loss of control of the 

aeroplane. 

For the reasons described above, this AD 

requires repetitive inspections and, 

depending on findings, replacement of the 

nose plate. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Grob Aircraft has issued Service 

Bulletin No. MSB817–58 and Service 

Bulletin No. MSB 817–060, both dated 

November 24, 2011, Repair Instruction 

Doc. No. RI 817–009, issue date 

November 17, 2011, and Repair 

Instruction Doc. No. RI 817–010/1, issue 

date December 20, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 59 products of U.S. registry. 

We also estimate that it would take 

about 6 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $424 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $55,106, or $934 per 

product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 12 work-hours and require parts 

costing $243, for a cost of $1,263 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
16970 Federal Register / Vol. 77, No. 57 / Friday, March 23, 2012 / Proposed Rules 

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), 

(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 adding 

the following new AD: 

Burkhart GROB Luft- und Raumfahrt GmbH: 

Docket No. FAA–2012–0324; Directorate 

Identifier 2012–CE–008–AD. 

(a) Comments Due Date 

We must receive comments by May 7, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Burkhart GROB Luftund Raumfahrt GmbH Models GROB G 109 

and GROB G 109B powered sailplanes, all 

serial numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 55: Stabilizer. 

(e) Reason 

This AD results from mandatory 

continuing airworthiness information (MCAI) 

originated 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 excessive 

corrosion on the nose plate in the vertical 

stabilizer. We are issuing this AD to detect 

and correct corrosion and flaking on the nose 

plate, which could cause the vertical 

stabilizer nose plate to fail and result in loss 

of control of the sailplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) Within 3 months after the effective date 

of this AD: 

(i) Inspect, from the top, the front and rear 

side of the nose plate, part number (P/N) 

109–2160.01, in the vertical stabilizer for 

corrosion and flaking following Part A of the 

Accomplishment Instructions in Grob 

Aircraft Service Bulletin No. MSB817–58, 

dated November 24, 2011. Repetitively 

thereafter inspect at intervals not to exceed 

12 months. 

(ii) Install an access panel on the left side 

of the vertical stabilizer following Grob 

Aircraft Repair Instruction Doc. No. RI 817– 

010/1, issue date December 20, 2011, as 

specified in Grob Aircraft Service Bulletin 

No. MSB 817–060, dated November 24, 2011. 

(iii) Through the access panel installed as 

required in paragraph (f)(1)(ii) of this AD, 

inspect, from below, the nose plate, P/N 109– 

2160.01, for corrosion and flaking following 

Part B of the Accomplishment Instructions in 

Grob Aircraft Service Bulletin No. MSB817– 

58, dated November 24, 2011. Repetitively 

thereafter inspect at intervals not to exceed 

12 months. 

(2) If any corrosion or flaking is found on 

the nose plate, P/N 109–2160.01, during any 

inspection required in paragraphs (f)(1)(i) or 

(f)(1)(iii) of this AD, replace P/N 109–2160.01 

with a serviceable part. Do the replacement 

following Grob Aircraft Repair Instruction 

Doc. No. RI 817–009, issue date November 

17, 2011, as specified in Grob Aircraft 

Service Bulletin No. MSB817–58, dated 

November 24, 2011. After replacement, 

continue with the repetitive inspections 

required in paragraphs (f)(1)(i) and (f)(1)(iii) 

of this AD. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any sailplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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: For any 

reporting requirement in this AD, 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. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EAS) AD No. 2012–0027, dated 

February 14, 2012; Grob Aircraft Service 

Bulletin No. MSB817–58 and Grob Aircraft 

Service Bulletin No. MSB 817–060, both 

dated November 24, 2011; Grob Aircraft 

Repair Instruction Doc. No. RI 817–009, issue 

date November 17, 2011; and Grob Aircraft 

Repair Instruction Doc. No. RI 817–010/1, 

issue date December 20, 2011 for related 

information. For service information related 

to this AD, contact Grob Aircraft AG, 

Lettenbachstrasse 9, D–86874 TussenhausenMattsies, Germany; telephone: +49 (0) 8268 

998139; fax: +49 (0) 8268 998200; email: 

productsupport@grob-aircraft.com; Internet: 

http://www.grob-aircraft.de.61.html. You 

may review copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. 

Issued in Kansas City, Missouri, on March 

19, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–7012 Filed 3–22–12; 8:45 am] 

BILLING CODE 4910–13–P 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS