37684 Federal Register / Vol. 76, No. 124 / Tuesday, June 28, 2011 / Proposed Rules 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2002–13–04, Amendment 39–12792 (67 

FR 43230, June 27, 2002), and adding 

the following new AD: 

Teledyne Continental Motors (TCM) and 

Rolls-Royce Motors Ltd. (R–RM) Series 

Reciprocating Engines: Docket No. FAA– 

2011–0085; Directorate Identifier 2000–NE– 

19–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by August 12, 2011. 

(b) Affected ADs 

This AD supersedes AD 2002–13–04, 

Amendment 39–12792. 

(c) Applicability 

This AD applies to TCM and R–RM C–125, 

C–145, O–300, IO–360, TSIO–360, and 

LTSIO–520–AE series reciprocating engines 

with Champion Aerospace (formerly Unison 

Industries) Slick Magnetos, models 6314, 

6324, and 6364, with magneto serial numbers 

(S/Ns) of 99110001 through 99129999 

inclusive. 

(d) Unsafe Condition 

This AD was prompted by an error in the 

previous AD applicability in the range of 

magneto S/Ns affected, and by the need to 

include certain engines made by R–RM, 

under license of TCM. We are issuing this AD 

to prevent engine failure and loss of control 

of the airplane due to migration of the 

magneto impulse coupling stop pin out of the 

magneto frame and into the gear train of the 

engine. 

(e) Compliance 

Comply with this AD within 10 flight 

hours after the effective date of this AD, 

unless already done. 

(f) Replacement of Magneto 

Replace any magneto that has a S/N of 

99110001 through 99129999, inclusive, with 

a magneto that does not have a serial number 

in that range. If magneto is not in this S/N 

range, no further action is required by this 

AD. 

(g) Inspections 

Inspect each removed magneto to verify 

that the impulse coupling stop pin is present. 

If the pin is missing, do the following: 

(1) For C–125, C–145, O–300, IO–360, and 

TSIO–360 series engines, do the following: 

(i) Remove magnetos, alternator or 

generator, and starter adapter from the 

accessory case. 

(ii) Remove the accessory case from the 

crankcase and oil sump. 

(iii) Visually inspect the entire engine gear 

train for damaged or broken gears and gear 

teeth. 

(iv) Inspect visible portions of the engine 

crankcase and accessory case for damage due 

to the stop pin becoming lodged between the 

engine gear train and the crankcase or 

accessory case. 

(v) If the accessory case is damaged, repair 

or replace the accessory case. 

(vi) If the engine crankcase is damaged, 

disassemble the engine, and repair or replace 

the crankcase. 

(vii) Inspect the oil pump drive gear teeth 

and inner cam gear teeth for damage. Replace 

any engine drive train component that has 

been damaged. 

(viii) Replace any damaged gear, and 

magnaflux the mating gears using the 

applicable engine overhaul manual. 

(2) For LTSIO–520–AE series engines, do 

the following: 

(i) Remove the starter adapter, fuel pump, 

vacuum pumps, accessory drive pads, and 

both magnetos. 

(ii) Visually inspect the entire engine gear 

train for damaged or broken gears and gear 

teeth. 

(iii) If any damage has occurred, remove 

the engine from the airplane, disassemble the 

engine, and inspect it for damage. If any 

damage is found, repair as necessary. 

(iv) Replace any damaged gear, and 

magnaflux the mating gears using the 

applicable engine overhaul manual. 

(v) Inspect the interior portions of the 

engine crankcase for damage due to the stop 

pin becoming lodged between the gear train 

and the crankcase. If the crankcase is 

damaged, repair or replace the crankcase. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install any Champion Aerospace (formerly 

Unison Industries) Slick magnetos, model 

6314, 6324, or 6364 that have a S/N of 

99110001 through 99129999 inclusive, on 

any engine. 

(i) Alternative Methods of Compliance 

The Manager, Atlanta Aircraft Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

(j) Related Information 

(1) A cross-reference for part numbers (P/ 

Ns) for Champion Aerospace (formerly 

Unison Industries) Slick magneto model 6314 

(TCM P/N 653271), model 6324 (TCM P/N 

653292), and model 6364 (TCM P/N 649696) 

can be found in TCM Mandatory Service 

Bulletin MSB00–6D, dated November 19, 

2010. 

(2) For more information about this AD, 

contact Neil Duggan, Aerospace Engineer, 

Propulsion, Atlanta Aircraft Certification 

Office, FAA, Small Airplane Directorate; 

1701 Columbia Avenue, College Park, 

Georgia, 30337; phone: (404) 474–5576; fax: 

(404) 474–5606; e-mail: neil.duggan@faa.gov. 

Issued in Burlington, Massachusetts, on 

June 20, 2011. 

Peter A. White, 

Acting Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–16088 Filed 6–27–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0687; Directorate 

Identifier 2011–CE–017–AD] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Model 

(Diamond) DA 40 Airplanes Equipped 

With Certain Cabin Air Conditioning 

Systems 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD would require deactivation and 

removal of the vapor cycle system (VCS) 

installed per STC SA03674AT held by 

Premier Aircraft Services (originally 

held by DER Services) following DER 

Services Master Document List MDL– 

2006–020–1, Revision C, dated February 

3, 2009; Revision D, dated April 22, 

2009; Revision E, dated May 12, 2010; 

or Revision F, dated July 6, 2010. This 

proposed AD would also require 

revision to the airplane weight and 

balance. This proposed AD was 

prompted by reports of damage around 

the VCS compressor mounting areas 

found during maintenance inspections. 

We are proposing this AD to remove the 

VCS mount, which could result in the 

air conditioner compressor 


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Federal Register / Vol. 76, No. 124 / Tuesday, June 28, 2011 / Proposed Rules 37685 

disconnecting in the engine 

compartment. This condition could 

result in engine stoppage or additional 

damage to the engine. 

DATES: We must receive comments on 

this proposed AD by August 12, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Premier 

Aircraft Service, 5540 NW. 23 Avenue 

Hangar 14, Ft. Lauderdale, FL 33309, 

telephone: (954) 771–0411; fax: (954) 

334–1489; Internet: http:// 

www.flypas.com. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust St., 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 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Hal 

Horsburgh, Aerospace Engineer, FAA, 

Atlanta Aircraft Certification Office, 

1701 Columbia Avenue, College Park, 

Georgia 30337; telephone: (404) 474– 

5553; fax: (404) 474–5606; e-mail: 

hal.horsburgh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–0687, Directorate Identifier 2011– 

CE–017–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 

We received reports of damage found 

during maintenance inspections of the 

Diamond Model DA 40 airplanes 

equipped with a VCS installed per 

Premier Aircraft Service STC 

SA03674AT held by Premier Aircraft 

Services (originally held by DER 

Services) following DER Services Master 

Document List MDL–2006–020–1, 

Revision C, dated February 3, 2009; 

Revision D, dated April 22, 2009; 

Revision E, dated May 12, 2010; or 

Revision F, dated July 6, 2010. The 

damage included excessive wear in the 

VCS compressor mounting holes, 

mounting brackets, and the mounting 

bolt, and denting was found around the 

mounting bracket and compressor due 

to unintended relative motion. We are 

proposing this AD to remove the VCS 

mount, which could result in the air 

conditioner compressor disconnecting 

in the engine compartment. This 

condition could result in engine 

stoppage or additional damage to the 

engine. 

Relevant Service Information 

We reviewed Premier Aircraft Service 

Work Instruction PAS–WI–MSB–40– 

2011–001, dated March 4, 2011; and 

Premier Aircraft Service Mandatory 

Service Bulletin No. PAS–MSB–40– 

2011–001, dated March 4, 2011. The 

service information describes 

procedures for deactivation of the VCS 

Compressor and associated mounting 

hardware and the removal of the VCS 

installed per Premier Aircraft Service 

STC SA03674AT. 

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 require 

deactivation of the VCS Compressor and 

removal of the VCS and the associated 

mounting hardware, except as discussed 

under ‘‘Differences Between the 

Proposed AD and the Service 

Information.’’ 

Differences Between the Proposed AD 

and the Service Information 

The service information requires 

compliance prior to flight after 

effectivity of the service information. 

The service information also includes a 

reporting requirement. 

This proposed AD requires a 

compliance time of within the next 100 

hours time-in-service after installation 

of the STC or 30 days after the effective 

date of this proposed AD, whichever 

occurs later. We are not including the 

reporting requirement. 

Costs of Compliance 

We estimate that this proposed AD 

affects 11 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Remove the VCS compressor, deactivate system, 

and revise weight and balance.

3 work-hours × $85 per 

hour = $255 

Not applicable .................. $255 $2,805 

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, 


emcdonald on DSK2BSOYB1PROD with PROPOSALS
37686 Federal Register / Vol. 76, No. 124 / Tuesday, June 28, 2011 / Proposed Rules 

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 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): 

Diamond Aircraft Industries GmbH Model 

(Diamond) DA 40 Airplanes Equipped 

With Certain Cabin Air Conditioning 

Systems: Docket No. FAA–2011–0687; 

Directorate Identifier 2011–CE–017–AD. 

Comments Due Date 

(a) We must receive comments by August 

12, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Diamond Aircraft 

Industries GmbH Model DA 40 airplanes, all 

serial numbers that: 

(1) Are equipped with vapor cycle system 

(VCS) cabin air conditioning systems 

installed per Premier Aircraft Services 

Supplemental Type Certificate (STC) 

SA03674AT following DER Services Master 

Document List MDL–2006–020–1, Revision 

C, dated February 3, 2009; Revision D, dated 

April 22, 2009; Revision E, dated May 12, 

2010; or Revision F, dated July 6, 2010; and 

(2) Are certificated in any category. 

Subject 

(d) Joint Aircraft System Component 

(JASC) Code 2150, Cabin Cooling System. 

Unsafe Condition 

(e) This AD was prompted by reports of 

damage around the VCS compressor 

mounting area found during maintenance 

inspections. We are proposing this AD to 

remove the VCS compressor and mount, as 

a result of excessive wear, which could result 

in the air conditioner compressor 

disconnecting in the engine compartment. 

This condition could result in engine 

stoppage or additional damage to the engine. 

Compliance 

(f) Comply with this AD within the 

compliance times specified, unless already 

done. 

Required Actions 

(g) Within the next 100 hours time-inservice after installation of the VCS installed 

per STC SA03674AT held by Premier 

Aircraft Services (originally held by DER 

Services) following DER Services Master 

Document List MDL–2006–020–1, Revision 

C, dated February 3, 2009; Revision D, dated 

April 22, 2009; Revision E, dated May 12, 

2010; or Revision F, dated July 6, 2010, or 

within 30 days after the effective date of this 

AD, whichever occurs later, do the following 

actions following Premier Aircraft Service 

Work Instruction PAS–WI–MSB–40–2011– 

001, dated March 4, 2011; and Premier 

Aircraft Service Mandatory Service Bulletin 

No. PAS–MSB–40–2011–001, dated March 4, 

2011: 

(1) Deactivate the VCS system. 

(2) Pull and collar the compressor breaker 

and place a placard above the breaker stating 

‘‘INOP.’’ 

(3) Remove the VCS compressor and 

associated mounting hardware. 

(4) Revise the airplane weight and balance. 

Special Flight Permit 

(h) The compressor drive belt must be cut 

and removed before the airplane may be 

moved for one ferry flight to an approved 

repair facility to comply with the remainder 

of this proposed AD. 

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, Atlanta Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

Related Information 

(j) For more information about this AD, 

contact Hal Horsburgh, Aerospace Engineer, 

FAA, Atlanta ACO, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5553; fax: (404) 474–5606; e-mail: 

hal.horsburgh@faa.gov. 

(k) For service information identified in 

this AD, contact Premier Aircraft Service, 

5540 NW. 23 Avenue Hangar 14, Ft. 

Lauderdale, FL 33309, telephone: (954) 771– 

0411; fax: (954) 334–1489; Internet: http:// 

www.flypas.com. You may review copies of 

the referenced service information at the 

FAA, Small Airplane Directorate, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (816) 329–4148. 

Issued in Kansas City, Missouri, on June 

22, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–16137 Filed 6–27–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employment and Training 

Administration 

20 CFR Part 655 

RIN 1205–AB61 

Wage Methodology for the Temporary 

Non-Agricultural Employment H–2B 

Program; Amendment of Effective Date 

AGENCY: Employment and Training 

Administration, Labor. 

ACTION: Proposed rule; request for 

comments. 

SUMMARY: The Department of Labor (the 

Department or DOL) proposes to amend 

the effective date of Wage Methodology 

for the Temporary Non-agricultural 

Employment H–2B Program; Final Rule, 

76 FR 3452, January 19, 2011, (the Wage 

Rule). The Wage Rule revised the 

methodology by which the Department 

calculates the prevailing wages to be 


emcdonald on DSK2BSOYB1PROD with PROPOSALS