This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

51999 

Vol. 70, No. 169 

Thursday, September 1, 2005 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2004–19694; Directorate 

Identifier 2004–CE–41–AD; Amendment 39– 

14240; AD 2005–17–19] 

RIN 2120–AA64 

Airworthiness Directives; Cirrus 

Design Corporation Models SR20 and 

SR22 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Cirrus Design Corporation (CDC) Models 

SR20 and SR22 airplanes. This AD 

requires you to measure and adjust the 

crew seat break-over bolts and to replace 

the crew seat recline locks on both crew 

seats. This AD results from CDC 

discovering that the crew seats, under 

emergency landing dynamic loads, may 

fold forward at less than the 26 g 

required by the regulations. We are 

issuing this AD to prevent the crew 

seats from folding forward during 

emergency landing dynamic loads with 

consequent occupant injury. 

DATES: This AD becomes effective on 

October 13, 2005. 

As of October 13, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Cirrus Design Corporation, 4515 

Taylor Circle, Duluth, Minnesota 55811; 

telephone: (218) 727–2737; Internet 

address: http://www.cirrusdesign.com. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590– 

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2004–19694; Directorate Identifier 

2004–CE–41–AD. 

FOR FURTHER INFORMATION CONTACT ONE

OF THE FOLLOWING: 

—Wess Rouse, Small Airplane Project 

Manager, ACE–117C, Chicago Aircraft 

Certification Office, 2300 East Devon 

Avenue, Room 107, Des Plaines, 

Illinois 60018; telephone: 847–294– 

8113; facsimile: (847) 294–7834; 

email: Wess.Rouse@faa.gov; or 

—Angie Kostopoulos, Composite 

Technical Specialist, ACE–116C, 

Chicago Aircraft Certification Office, 

2300 East Devon Avenue, Room 107, 

Des Plaines, Illinois 60018; telephone: 

(847) 294–7426; facsimile: (847) 294– 

7834; e-mail: 

Evangelia.Kostopoulos@Faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? 

The Cirrus Design Corporation (CDC) 

performed dynamic seat testing on 

Models SR20 and SR22 airplanes. CDC 

found that, under emergency landing 

dynamic loads, the crew seats may fold 

forward at less than the 26 g required by 

14 CFR Section 23.562(b)(2). 

What is the potential impact if FAA 

took no action? If not prevented, the 

crew seats folding forward during 

emergency landing dynamic loads could 

result in occupant injury. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to certain 

Cirrus Design Corporation (CDC) Models 

SR20 and SR22 airplanes. This proposal 

was published in the Federal Register 

as a notice of proposed rulemaking 

(NPRM) on January 13, 2005 (70 FR 

2370). The NPRM proposed to measure 

and adjust the crew seat break-over bolts 

and to replace the crew seat recline 

locks on both crew seats. Since issuing 

the earlier NPRM, FAA received and 

evaluated new service information that 

increases the serial number effectivity of 

the earlier NPRM. Since the change 

imposed an additional burden over that 

proposed in the earlier NPRM, we 

reopened the comment period to allow 

the public additional time to comment 

on the proposed AD. The supplemental 

NPRM was published in the Federal 

Register on June 9, 2005 (70 FR 33724). 

Comments 

Was the public invited to comment? 

We again provided the public the 

opportunity to participate in developing 

this AD. We received no comments on 

the supplemental NPRM or on the 

determination of the cost to the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

1,501 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? CDC will provide warranty 

credit for service bulletins SB A2X–25– 

08, dated June 22, 2004, and SB 2X–25– 

06 R4, dated May 5, 2005. This AD will 

not have a labor or parts cost for the 

owner or operator. 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 

52000 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 

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 AD. 

Regulatory Findings 

Will this AD impact various entities? 

We have 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. 

Will this AD involve a significant rule 

or regulatory action? 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 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 summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Impact) and placed it in the 

AD Docket. You may get a copy of this 

summary by sending a request to us at 

the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2004–19694; 

Directorate Identifier 2004–CE–41–AD’’

in your request. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2005–17–19 Cirrus Design Corporation: 

Amendment 39–14240; Docket No. 

FAA–2004–19694; Directorate Identifier 

2004–CE–41–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on October 

13, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects the following airplane 

models and serial numbers that are 

certificated in any category: 

Model Serial Nos. 

(1) SR20 ........ 1005 through 1455. 

(2) SR22 ........ 0002 through 1044. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of discovering that 

the crew seats, under emergency landing 

dynamic loads, may fold forward at less than 

26 g required by the regulations, 14 Code of 

Federal Regulations (CFR) Section 

23.562(b)(2). The actions specified in this AD 

are intended to prevent the crew seats from 

folding forward during emergency landing 

dynamic loads with consequent occupant 

injury. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following: 

Actions Compliance Procedures 

(1) For Models SR20, serial numbers 1005 through 1423, 

and SR22, serial numbers 0002 through 0972, do the following actions: 

(i) Move the lower portion of the crew seat upholstery 

upward to expose the seat frame and locking mechanism. Measure the clearance between the break-over 

bolt and the seat frame for a clearance that meets 

the requirements in the service bulletin.

(ii) If the clearance does not meet that specified in the 

service bulletin, do the crew seat break-over bolt adjustment and re-cover the crew seat frame and locking mechanism with the upholstery.

(iii) If the clearance does meet that specified in the 

service bulletin, re-cover the crew seat frame and 

locking mechanism.

(iv) Repeat the above actions for the opposite crew seat 

Within 50 hours time-in-service (TIS) or 

within 180 days, whichever occurs 

first after October 13, 2005 (the effective date of this AD).

Follow Cirrus Design Corporation Alert 

Service Bulletin SB A2X–25–08, 

dated June 22, 2004. 

Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 52001 

Actions Compliance Procedures 

(2) For Models SR20, serial numbers 1005 through 1455, 

and SR22, serial numbers 0002 through 1044, do the following actions: 

(i) Identify whether the recline lock is secured with two 

bolts or three bolts.

(ii) If the recline locks are secured with two bolts, remove the existing recline locks and replace with the 

new recline locks kit, kit number 70084–001.

(iii) If the recline locks are secured with three bolts, remove existing recline locks and replace with the new 

recline locks kit, kit number 70084–002.

(iv) Check break-over pin alignment and adjust as necessary.

(v) Check that the locks engage with the break-over 

bolts with the seat in the full recline position. If full 

seat recline is not possible or difficult to engage, 

grinding of the lower aft seat frame is necessary.

(vi) Repeat the above actions for the opposite crew seat 

Within 50 hours TIS or within 180 days, 

whichever occurs first after October 

13, 2005 (the effect9ve date of this 

AD).

Follow Cirrus Design Corporation Service Bulletin SB 2X–25–06 R4, revised 

May 5, 2005. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Chicago Aircraft Certification 

Office, FAA. For information on any already 

approved alternative methods of compliance, 

please contact one of the following: 

(1) Wess Rouse, Small Airplane Project 

Manager, ACE–117C; Chicago Aircraft 

Certification Office, 2300 East Devon 

Avenue, Roon 107, Des Plaines, Illinois 

60018; telephone: (847) 294–8113; facsimile: 

(847) 294–7834; e-mail: 

Wess.Rouse@Faa.gov; or 

(2) Angie Kostopoulos, Aerospace 

Engineer, ACE–116C, Chicago Aircraft 

Certification Office, 2300 East Devon 

Avenue, Room 107, Des Plaines, Illinois 

60018; telephone: (847) 294–7426; facsimile: 

(847) 294–7834; e-mail: 

Evangelia.Kostopoulos@Faa.gov. 

Does This AD Incorporate Any Material by 

Reference? 

(g) You must do the actions required by 

this AD following the instructions in Cirrus 

Design Corporation Alert Service Bulletin SB 

A2X–25–08, dated June 22, 2004; and Service 

Bulletin SB 2X–25–06 R4, revised May 5, 

2005. The Director of the Federal Register 

approved the incorporation by reference of 

these service bulletins in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. To get a 

copy of this service information, contact 

Cirrus Design Corporation, 4515 Taylor 

Circle, Duluth, Minnesota 55811; telephone: 

(218) 727–2737; Internet address: http:// 

www.cirrusdesign.com. To review copies of 

this service information, go to the National 

Archives and Records Administration 

(NARA). For information on the availability 

of this material at NARA, go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2004–19694; Directorate Identifier 2004–CE–

41–AD. 

Issued in Kansas City, Missouri, on August 

19, 2005. 

Terry L. Chasteen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–16980 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 98–ANE–61–AD; Amendment 

39–14243; AD 2005–18–03] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney PW2000 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Pratt & Whitney (PW) PW2000 series 

turbofan engines. That AD currently 

requires revisions to the engine 

manufacturer’s time limits section (TLS) 

to include enhanced inspection of 

selected critical life-limited parts at 

each piece-part opportunity. This AD 

requires modifying the airworthiness 

limitations section of the manufacturer’s 

manual and an air carrier’s approved 

continuous airworthiness maintenance 

program to incorporate additional 

inspection requirements. This AD 

results from an FAA study of in-service 

events involving uncontained failures of 

critical rotating engine parts that 

indicates the need for mandatory 

inspections. The mandatory inspections 

are needed to identify those critical 

rotating parts with conditions, which if 

allowed to continue in service, could 

result in uncontained failures. We are 

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

which could result in an uncontained 

engine failure and damage to the 

airplane. 

DATES: This AD becomes effective 

February 28, 2006. 

ADDRESSES: You may examine the AD 

docket at the FAA, New England 

Region, Office of the Regional Counsel, 

12 New England Executive Park, 

Burlington, MA. 

FOR FURTHER INFORMATION CONTACT: 

Mark Riley, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7758, fax 

(781) 238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to PW 

PW2000 series turbofan engines. We 

published the proposed AD in the 

Federal Register on August 18, 2004 (69 

FR 51198). That action proposed to 

require modifying the TLS of the 

manufacturer’s manual and an air 

carrier’s approved continuous 

airworthiness maintenance program to 

incorporate the additional inspection 

requirements. 

Examining the AD Docket 

You may examine the AD Docket 

(including any comments and service 

information), by appointment, between 

8 a.m. and 4:30 p.m., Monday through