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.

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REGISTER issue of each week.

Rules and Regulations Federal Register

19873 

Vol. 74, No. 82 

Thursday, April 30, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0395; Directorate 

Identifier 2009–CE–023–AD; Amendment 

39–15895; AD 2009–09–09] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company (Type Certificate 

Previously Held by Columbia Aircraft 

Manufacturing (Previously The Lancair 

Company)) Models LC40–550FG, 

LC41–550FG, and LC42–550FG 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Type 

Certificate previously held by Columbia 

Aircraft Manufacturing (previously The 

Lancair Company)) Models LC40– 

550FG, LC41–550FG, and LC42–550FG 

airplanes. This AD requires you to 

repetitively inspect the rudder hinges 

and the rudder hinge brackets for 

damage, i.e., cracking, deformation, and 

discoloration. If damage is found during 

any inspection, this AD also requires 

you to replace the damaged rudder 

hinge and/or rudder hinge bracket. This 

AD results from reports that cracked 

lower rudder hinge brackets were found 

on two of the affected airplanes. We are 

issuing this AD to detect and correct 

damage in the rudder hinges and the 

rudder hinge brackets, which could 

result in failure of the rudder. This 

failure could lead to loss of control. 

DATES: This AD becomes effective on 

May 11, 2009. 

On May 11, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by June 29, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• 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. 

To get the service information 

identified in this AD, contact Cessna 

Aircraft Company, Product Support, 

P.O. Box 7706; Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax: (316) 

942–9006; Internet: http:// 

www.cessna.com. 

To view the comments to this AD, go 

to http://www.regulations.gov. The 

docket number is FAA–2009–0395; 

Directorate Identifier 2009–CE–023–AD. 

FOR FURTHER INFORMATION CONTACT: Gary 

Park, Aerospace Engineer, Wichita 

Aircraft Certification Office (ACO), 1801 

Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946– 

4123; fax: (316) 946–4107; e-mail: 

gary.park@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We have received reports that a 

cracked lower rudder hinge bracket was 

found on two Cessna Aircraft Company 

Model LC41–550FG airplanes. 

One of the airplanes had 106 hours 

time-in-service (TIS) and the rudder 

hinge was fully fractured. The other 

airplane had 225 hours TIS and the 

rudder hinge was partially fractured. 

The cracks occurred because of 

corrosion of the anodized 2024 

aluminum brackets. By design, the 

bearings are pressed into hinge elements 

and then staked on either side. In the 

staking process, the anodized protection 

is lost. 

Investigation is ongoing to determine 

to the best approach to take to 

incorporate a modification or a design 

change to prevent the rudder hinges and 

the rudder hinge brackets from 

becoming damaged, i.e., cracked, 

deformed, and discolored. 

This condition, if not corrected, could 

result in failure of the rudder. This 

failure could lead to loss of control. 

Relevant Service Information 

We reviewed Cessna Aircraft 

Company Single Engine Service Bulletin 

SB09–27–01, dated April 13, 2009. The 

service information describes 

procedures for repetitively inspecting 

the rudder hinges and the rudder hinge 

brackets for damage, i.e., cracking, 

deformation, and discoloration. The 

service information also describes 

procedures for replacing any damaged 

rudder hinge and/or rudder hinge 

bracket. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This AD requires 

repetitively inspecting the rudder 

hinges and the rudder hinge brackets for 

damage. If damage is found during any 

inspection, this AD also requires 

replacing the damaged rudder hinge 

and/or rudder hinge bracket. 

Cessna Aircraft Company is reviewing 

the information related to the 

occurrences referenced in this AD and 

may develop a modification that, when 

incorporated, would eliminate the need 

for the repetitive inspections required 

by this AD. The FAA will review any 

modification that is developed, 

determine whether it would eliminate 

the need for the requirements of this 

action, and then determine whether 

additional AD action is necessary. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because rudder failure could lead to 

loss of control. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

19874 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules and Regulations 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and an 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include the docket number ‘‘FAA– 

2009–0395; Directorate Identifier 2009– 

CE–023–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the AD in light 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 

concerning this AD. 

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 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. 

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 

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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket that 

contains the AD, the regulatory 

evaluation, any comments received, and 

other information 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 Docket Office (telephone (800) 647– 

5527) is located at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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 FAA amends 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): 

2009–09–09 Cessna Aircraft Company 

(Type Certificate previously held by 

Columbia Aircraft Manufacturing 

(previously The Lancair Company)): 

Amendment 39–15895; Docket No. 

FAA–2009–0395; Directorate Identifier 

2009–CE–023–AD. 

Effective Date 

(a) This AD becomes effective on May 11, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

Model Serial Nos. 

LC40–550FG 40001 through 40079. 

LC41–550FG 41001 through 41800, 411001 

and subsequent. 

LC42–550FG 42001 through 42569, 421001 

and subsequent. 

Unsafe Condition 

(d) This AD is the result of reports that 

cracked lower rudder hinge brackets were 

found on two of the affected airplanes. We 

are issuing this AD to detect and correct 

damage, i.e., cracking, deformation, and 

discoloration, in the rudder hinges and the 

rudder hinge brackets, which could result in 

failure of the rudder. This failure could lead 

to loss of control. 

Compliance 

(e) To address this problem, you must do 

the following per Cessna Aircraft Company 

Single Engine Service Bulletin SB09–27–01, 

dated April 13, 2009, unless already done: 

Condition Initial inspection Repetitive inspection 

(1) For airplanes with 25 hours time-in-service 

(TIS) or more as of May 11, 2009 (the effective date of this AD): 

With the rudder removed and using 10X visual magnification, inspect all three rudder 

hinges and rudder hinge brackets for damage, i.e., cracking, deformation, and discoloration, at whichever of the following occurs 

first: 

(i) Within the next 10 hours TIS after May 11, 

2009 (the effective date of this AD); or 

(ii) Within the next 30 days after May 11, 

2009 (the effective date of this AD). 

Thereafter inspect as follows: 

(A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges 

and rudder hinge brackets for damage; and 

(B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed 

and using 10X visual magnification, inspect 

all three rudder hinges and rudder hinge 

brackets for damage. 

Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules and Regulations 19875 

Condition Initial inspection Repetitive inspection 

(2) For airplanes with less than 25 hours TIS as 

of May 11, 2009 (the effective date of this 

AD): 

Without removing the rudder, visually inspect 

all three rudder hinges and rudder hinge 

brackets for damage, at whichever of the 

following occurs later: 

(i) Upon accumulating 25 hours TIS; or 

(ii) Within the next 10 hours TIS after May 11, 

2009 (the effective date of this AD). 

Thereafter inspect as follows: 

(A) Every 25 hours TIS or 3 months, whichever occurs first, without removing the rudder, visually inspect all three rudder hinges 

and rudder hinge brackets for damage. 

(B) Every 50 hours TIS or 6 months, whichever occurs first, with the rudder removed 

and using 10X visual magnification, inspect 

all three rudder hinges and rudder hinge 

brackets for damage. 

(3) If damage is found on any of the rudder 

hinges and/or rudder hinge brackets during 

any inspection required in paragraphs (e)(1) 

or (e)(2), before further flight, replace the 

damaged rudder hinges and/or rudder hinge 

brackets with new parts and inspect 

following the Repetitive Inspection 

procedures specified in paragraphs (e)(1) or 

(e)(2) of this AD. 

(4) If the repetitive inspections required in 

paragraphs (e)(1) and (e)(2) of this AD 

become due at the same time, credit for both 

inspections will be given by doing the rudder 

removal and 10X visual inspection. 

(5) Use the form (Figure 1 of this AD) to 

report the results of the following inspections 

required in this AD to the FAA at the address 

specified in paragraph (f) of this AD: 

(i) Initial inspections required in 

paragraphs (e)(1) and (e)(2) of this AD, report 

within 10 days after the inspection or within 

10 days of May 11, 2009 (after the effective 

date of this AD), whichever occurs later. 

(ii) Repetitive inspections required in 

paragraphs (e)(1) and (e)(2) of this AD ONLY 

if cracks are found, report within 10 days 

after the inspection. 

(iii) The Office of Management and Budget 

(OMB) approved the information collection 

requirements contained in this regulation 

under the provisions of the Paperwork 

Reduction Act of 1980 (44 U.S.C. 3501 et 

seq.) and assigned OMB Control Number 

2120–0056. 

AD 2009–09–09 Inspection Report 

Airplane Model 

Airplane Serial Number 

Airplane Tach Hours at Time of Inspection 

Is Upper Rudder Bracket Damaged? No Yes, describe extent of damage 

Is Middle Rudder Bracket Damaged? No Yes, describe extent of damage 

Is the Lower Rudder Bracket Damaged? (Models LC40–550FG & 

LC42–550FG only) 

No Yes, describe extent of damage 

Is Lower Rudder Hinge Damaged? (Model LC40–550FG) No Yes, describe extend of damage 

Were any other discrepancies noticed during the inspection? 

Name: 

Telephone and/or e-mail address: 

Date: 

Send report to: Gary Park, Aerospace Engineer, ACE–118W, Wichita 

Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; fax: (316) 946–4107; e-mail: gary.park@faa.gov. 

Figure 1 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita 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. Send information to Attn: Gary 

Park, Aerospace Engineer, ACE–118W, 

Wichita Aircraft Certification Office (ACO), 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; telephone: (316) 946–4123; 

fax: (316) 946–4107; e-mail: 

gary.park@faa.gov. Before using any airplane 

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. 

Material Incorporated by Reference 

(g) You must use Cessna Aircraft Company 

Single Engine Service Bulletin SB09–27–01, 

dated April 13, 2009, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Cessna Aircraft Company, 

Product Support, P.O. Box 7706; Wichita, 

Kansas 67277; telephone: (316) 517–5800; 

fax: (316) 942–9006; Internet: http:// 

www.cessna.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

19876 Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules and Regulations 

Issued in Kansas City, Missouri, on April 

23, 2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–9793 Filed 4–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2007–0391; Directorate 

Identifier 2007–NM–271–AD; Amendment 

39–15891; AD 2009–09–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A318–100 and A319–100 Series 

Airplanes; A320–111 Airplanes; A320– 

200 Series Airplanes; and A321–100 

and A321–200 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Airbus Model 

A318–100 and A319–100 series 

airplanes; A320–111 airplanes; A320– 

200 series airplanes; and A321–100 and 

A321–200 series airplanes. That AD 

currently requires a one-time inspection 

of the horizontal hinge pin of the 103VU 

electrical panel in the avionics 

compartment to determine if the hinge 

pin can move out of the hinge, and 

related investigative and corrective 

actions if necessary. This new AD 

instead requires installing a hinge pin 

stopper on the internal door of the 

103VU electrical panel. This AD results 

from a report indicating that electrical 

wire damage was found in the 103VU 

electrical panel due to contact between 

the hinge pin and the adjacent electrical 

wire harness. We are issuing this AD to 

prevent contact between the horizontal 

hinge pin and the adjacent electrical 

wire harness, which could result in 

damage to electrical wires, and 

consequent arcing and/or failure of 

associated systems. 

DATES: This AD becomes effective June 

4, 2009. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 4, 2009. 

ADDRESSES: For service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; e-mail: 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the Document Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tim 

Dulin, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–2141; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–03–10, amendment 

39–14474 (71 FR 6665, February 9, 

2006). The existing AD applies to 

certain Airbus Model A318–100 and 

A319–100 series airplanes; A320–111 

airplanes; A320–200 series airplanes; 

and A321–100 and A321–200 series 

airplanes. That NPRM was published in 

the Federal Register on January 9, 2008 

(73 FR 1558). That NPRM proposed to 

discontinue the existing requirements 

and instead require installing a hinge 

pin stopper on the internal door of the 

103VU electrical panel. This AD results 

from a report indicating that electrical 

wire damage was found in the 103VU 

electrical panel due to contact between 

the hinge pin and the adjacent electrical 

wire harness. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request for Additional Action 

The Air Transport Association (ATA), 

on behalf of one of its members, 

Northwest Airlines (NWA), notes that 

the proposed modification prevents 

only outboard migration of the pins, and 

requests that the AD be changed to 

require a hinge pin stopper to be added 

to both ends of the hinge to completely 

contain the hinge pin and prevent 

inboard migration. 

We do not agree with ATA’s request. 

We are issuing this AD to address 

potential wire damage due to outboard 

migration of the hinge pin. There is no 

potential of wire damage due to inboard 

migration of the pin. However, if 

additional data show that inboard 

migration of the hinge pin causes an 

unsafe condition, we might consider 

further rulemaking. We have not 

changed the AD in this regard. 

Request for Alternate Modification 

The ATA, on behalf of NWA, requests 

that the AD be changed to allow the 

hinge stoppers to be installed using the 

existing hole in the lower angle fitting 

(part number D92510153000) adjacent 

to the end hinge mounting hole, instead 

of drilling a new hole through the hinge 

assembly. NWA states that this change 

would eliminate the need for any 

drilling during modification, and would 

more easily facilitate accomplishment 

within the line maintenance 

environment, providing greater 

scheduling flexibility. 

We do not agree with ATA’s request. 

Airbus Mandatory Service Bulletin 

A320–25–1535, dated April 27, 2007, 

specifies drilling a hole on the hinge. 

The commenter did not provide 

sufficient data to substantiate that using 

the existing hole would address the 

identified unsafe condition. To use a 

different method from the one specified 

in that service bulletin, operators may 

request approval of an alternative 

method of compliance (AMOC) 

according to paragraph (g) of the AD. 

We have not changed the AD in this 

regard. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

This AD affects about 658 Airbus 

Model A318–100 and A319–100 series 

airplanes; A320–111 airplanes; A320– 

200 series airplanes; and A321–100 and 

A321–200 series airplanes of U.S. 

registry. The new actions take about 1 

work hour per airplane, at an average 

labor rate of $80 per work hour. 

Required parts cost about $20 per 

airplane. Based on these figures, the 

estimated cost of the new actions 

specified in this AD for U.S. operators 

is $65,800, or $100 per airplane.