Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules 67631 

TABLE 1—FACTORED HOURS TIS FOR A YOKE—Continued 

Helicopter model Types of operation 

Rate per hour of 

external load lifts and 

takeoffs 

Unfactored 

hours TIS 

Hours TIS 

factor 

Factored hours 

TIS on yoke 

(unfactored hours 

TIS × hours TIS 

factor) 

Internal Load Operations.All Takeoffs ............... 2,025 1 2,025 

Total Factored Hours TIS on Yoke 

(Summation of the Factored Hours 

TIS).

.................................... .................................... .................... .................... 3,450 

1For the purposes of this AD, an external load operation occurs each time a helicopter picks up an external load and drops it off. Any external 

load lift in which the helicopter achieves a vertical altitude difference of greater than 200 feet indicated attitude between the pick-up and drop-off 

point counts as two external load lifts in determining the proper rate per hour category. 

Note 1: The number of unfactored hours 

TIS and factored hours TIS contained in 

Table 1 of this AD are examples and 

presented for illustration purposes only. 

(4) By reference to Table 1 of this AD, enter 

the ‘‘Unfactored Hours TIS’’ for each category 

as determined by paragraph (a)(3) of this AD. 

Calculate the ‘‘Factored Hours TIS’’ by 

multiplying the ‘‘Unfactored Hours TIS’’ by 

the ‘‘Hours TIS Factor.’’ Determine the 

accumulated ‘‘Total Factored Hours TIS’’ on 

each yoke by adding the factored hours TIS 

for each type of operation and helicopter 

model. Tracking the Total Factored Hours 

TIS is only for establishing a retirement life 

and not for tracking inspection intervals. 

(5) Record the accumulated Total Factored 

Hours TIS on the component history card or 

equivalent record for each yoke. 

(6) Continue to factor the hours TIS for 

each yoke by following paragraph (a)(2) 

through (a)(4) of this AD, and record the 

additional factored hours TIS on the 

component history card or equivalent record. 

(b) For helicopters with yoke, P/N 204– 

011–102 (all dash numbers), installed, before 

further flight, unless accomplished 

previously: 

(1) For hours TIS accumulated before the 

effective date of this AD, calculate and record 

the Total Factored Hours TIS as follows: 

(i) For the Model 212 helicopters, 1 hour 

TIS in which passenger or internal cargo was 

carried equals 1 factored hour TIS; 1 hour 

TIS where more than 4 external load lifts 

occurred equals 5 factored hours TIS. 

(ii) For the Model 204 and 205 series 

helicopters, 1 hour TIS equals 1 factored 

hour TIS. 

Note 2: Paragraph (b)(1) gives credit to the 

operators for compliance with ADs 81–19–01 

and 81–19–02 in establishing the starting 

point for the new factoring of hours TIS 

contained in this AD. 

Note 3: The accumulated Total Factored 

Hours TIS for yoke, P/N 204–011–102 (all 

dash numbers), calculated in accordance 

with the applicable Bell Model 204B, 205A– 

1, 205B, or 212 maintenance manuals, which 

results in an equal or higher accumulated 

Total Factored Hours TIS is an acceptable 

alternative to meeting the factoring 

requirements of AD 81–19–01 (contained in 

Bell ASB 212–81–23, dated June 22, 1981, for 

the Model 212 helicopters) and AD 81–19– 

02 (contained in Bell ASBs 204–81–11 and 

205–81–16, both dated June 22, 1981, for the 

Model 204 and 205 series helicopters). 

(2) For hours TIS accumulated after the 

effective date of this AD, calculate and record 

the factored hours TIS on the yoke in 

accordance with the requirements of 

paragraphs (a)(1) thorough (a)(6) of this AD. 

(c) Revise the Airworthiness Limitations 

section of the applicable maintenance 

manuals or the Instructions for Continued 

Airworthiness (ICAs) by establishing a new 

retirement life of 3,600 Total Factored Hours 

TIS for each yoke, P/N AAI–4011–102 (all 

dash numbers), ASI–4011–102 (all dash 

numbers), or 204–011–102 (all dash 

numbers), by making pen and ink changes or 

inserting a copy of this AD into the 

Airworthiness Limitations section of the 

maintenance manual or ICAs. 

(d) Unless accomplished previously, record 

a life limit of 3,600 Total Factored Hours TIS 

for each yoke, P/N AAI–4011–102 (all dash 

numbers), ASI–4011–102 (all dash numbers), 

or 204–011–102 (all dash numbers), on the 

component history card or equivalent record. 

(e) Within 100 hours TIS or 600 hours TIS 

since the last magnetic particle inspection 

(MPI) of the yoke, whichever occurs later, 

and thereafter at intervals not to exceed 600 

hours TIS, for any yoke installed on any 

Model 205B or 212 helicopter: 

(1) Remove the yoke from the main rotor 

hub assembly (hub). Using a 5-power or 

higher magnifying glass, visually inspect 

each pillow block bushing hole, spindle 

radius, and center section web for any 

corrosion or mechanical damage. 

(2) Perform an MPI of each yoke for a 

crack. 

Note 4: MPI procedures are contained in 

Bell Standard Practices Manual BHT–ALL– 

SPM. 

(f) Within 100 hours TIS or 2,400 hours TIS 

since the last MPI of the yoke, whichever 

occurs later, and thereafter at intervals not to 

exceed 2,400 hours TIS, for any yoke 

installed on any Model 204B, 205A, or 205A– 

1 helicopter: 

(1) Remove the yoke from the hub. Using 

a 5-power or higher magnifying glass, 

visually inspect each pillow block bushing 

hole, spindle radius, and center section web 

for any corrosion or mechanical damage. 

(2) Perform an MPI of each yoke for a 

crack. 

(g) Before further flight, replace each yoke 

with an airworthy yoke if: 

(1) The yoke has 3,600 or more Total 

Factored Hours TIS; or 

(2) The Total Factored Hours TIS for the 

yoke is unknown and cannot be determined; 

or 

(3) The yoke has any corrosion or 

mechanical damage that exceeds any of the 

maximum repair damage limits; or 

Note 5: The applicable Bell Component 

and Repair Overhaul Manual contains the 

maximum repair damage limitations. 

(4) The yoke has a crack. 

(h) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Rotorcraft 

Certification Office, FAA, ATTN: Michael 

Kohner, Aviation Safety Engineer, Rotorcraft 

Directorate, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5170, fax (817) 222–5783, for information 

about previously approved alternative 

methods of compliance. 

(i) Special flight permits may only be 

issued under 14 CFR 21.197 and 21.199 for 

the purpose of operating the helicopter to a 

location where the MPI requirements of 

paragraphs (e) or (f) of this AD can be 

performed. 

(j) The Joint Aircraft System Component 

(JASC) Code is 6220: Main Rotor Head Issued 

in Fort Worth, Texas, on October 21, 2011. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28361 Filed 11–1–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1212; Directorate 

Identifier 2011–CE–034–AD] 

RIN 2120–AA64 

Airworthiness Directives; Cirrus 

Design Corporation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

67632 Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Cirrus Design Corporation (Cirrus) 

Model SR22T airplanes. This proposed 

AD was prompted by reports of partial 

loss of engine power due to a dislodged 

rubber gasket/seal being ingested into 

the turbocharger. This proposed AD 

would require inspection and 

modification of the air box flange welds 

and slots and installation of induction 

system air box seals as applicable. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by December 19, 

2011. 

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 Cirrus Design 

Corporation, 4515 Taylor Circle, Duluth, 

Minnesota 55811–1548, phone: (218) 

788–3000; fax: (218) 788–3525; email: 

fieldservice@cirrusaircraft.com; Internet: 

http://www.cirrusaircraft.com. 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 

(phone: (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Michael Downs, Propulsion Engineer, 

Chicago ACO, FAA, O’Hare Lake Office 

Center, 2300 East Devon Ave., Des 

Plaines, Illinois 60018; phone: (847) 

294–7870; fax: (847) 294–7834; email: 

michael.downs@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– 

2011–1212; Directorate Identifier 2011– 

CE–034–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 two reports of partial loss 

of engine power due to dislodged rubber 

gaskets/seals being ingested into one of 

the two turbochargers. The gasket/seal is 

located between the air-box mounting 

base and the turbochargers. Once the 

gasket/seal is ingested into a 

turbocharger the engine will experience 

a partial loss of power as the 

turbocharger fails to perform its 

function. A complete loss of power 

could occur if metal debris from the 

failing turbocharger migrates into the 

engine oil system and damages other 

engine components. Examination by 

Cirrus of other Cirrus Model SR22T 

airplanes showed early evidence of the 

gasket/seal starting to dislodge on at 

least one other airplane. 

This condition, if not corrected, could 

result in engine failure. 

Relevant Service Information 

We reviewed Cirrus Design 

Corporation SR22T Service Bulletin SB 

2X–71–17 R1, dated September 30, 

2011. The service information describes 

procedures for replacement of the air 

box seals. 

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 

inspection and modification of the air 

box flange welds and slots and 

installation of air box seals and adhesive 

with materials better suited for the hightemperature environment encountered 

in close proximity to the turbocharger. 

Costs of Compliance 

We estimate that this proposed AD 

affects 67 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 

Replacement of the induction system air box seals 

and extension of air box flange slots.

2.5 work-hours × $85 per hour = 

$212.50.

$139 $351.50 $23,550.50 

According to the manufacturer, all of 

the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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: 

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Federal Register / Vol. 76, No. 212 / Wednesday, November 2, 2011 / Proposed Rules 67633 

‘‘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): 

Cirrus Design Corporation: Docket No. FAA– 

2011–1212; Directorate Identifier 2011– 

CE–034–AD. 

(a) Comments Due Date 

We must receive comments by December 

19, 2011. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the following model 

and serial number airplanes, certificated in 

any category: 

(1) Group 1 Airplanes: Cirrus Design 

Corporation Model SR22T airplanes, serial 

numbers 0001 through 0169, except 0004, 

0019, 0027, 0047, 0097, 0126, 0127, 0135, 

0138, 0139, 0144, 0154, 0155, 0157, 0158, 

0159, 0160, 0161, and 0163. 

(2) Group 2 Airplanes: Cirrus Design 

Corporation Model SR22T airplanes, serial 

numbers 0004, 0019, 0027, 0047, 0097, 0126, 

0127, 0135, 0138, 0139, 0144, 0155, 0157, 

0158, 0160, and 0161. These airplanes had 

the reinforced silicone fiberglass seals 

installed at the factory but the box flange 

welds and slots may be incorrectly modified. 

Therefore, this AD still applies to these 

airplanes. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7160, Engine Air Intake. 

(e) Unsafe Condition 

This AD was prompted by reports of partial 

loss of engine power due to a dislodged 

rubber gasket/seal being ingested into the 

turbocharger. We are issuing this AD to 

inspect and modify the air box flange welds 

and slots and install induction system air box 

seals as applicable. 

(f) Compliance 

Comply with this AD following Cirrus 

Design Corporation SR22T Service Bulletin 

SB 2X–71–17 R1, dated September 30, 2011, 

within the compliance times specified, 

unless already done. 

(g) Actions 

(1) Group 1 Airplanes: Within the next 10 

hours time-in-service (TIS) after the effective 

date of this AD, inspect the air box flange 

welds and slots, make modifications as 

necessary, and replace the induction air box 

seals with reinforced silicone fiberglass seals 

part number 29486–001. 

(2) Group 2 Airplanes: Within the next 10 

hours TIS after the effective date of this AD, 

inspect the air box flange welds and slots 

and, as necessary, make modifications. 

Note: Credit will be given for actions 

required in paragraphs (g)(1) and (g)(2) of this 

AD if already done before the effective date 

of this AD following Cirrus Design 

Corporation SR22T Service Bulletin SB 2X– 

71–17, dated July 21, 2011. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Chicago 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. 

(i) Related Information 

(1) For more information about this AD, 

contact Michael Downs, Propulsion Engineer, 

Chicago ACO, FAA, O’Hare Lake Office 

Center, 2300 East Devon Ave., Des Plaines, 

Illinois 60018; phone: (847) 294–7870; fax: 

(847) 294–7834; email: 

michael.downs@faa.gov. 

(2) For service information identified in 

this AD, contact Cirrus Design Corporation, 

4515 Taylor Circle, Duluth, Minnesota 

55811–1548, phone: (218) 788–3000; fax: 

(218) 788–3525; email: 

fieldservice@cirrusaircraft.com; Internet: 

http://www.cirrusaircraft.com. 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 

October 27, 2011. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–28382 Filed 11–1–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1166; Directorate 

Identifier 2010–NM–169–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Model Mystere-Falcon 50 

Airplanes 

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 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: 

The Maintenance Procedure (MP) 57–607, 

related to non destructive check of the flap 

tracks 2 and 5, has been introduced thru 

revision 4 (01/2009) of section 5–10 of the 

Recommended Maintenance Schedules 

chapter of the Aircraft Maintenance 

Documentation. 

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