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

6523 

Vol. 76, No. 25 

Monday, February 7, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1152; Directorate 

Identifier 2009–CE–026–AD; Amendment 

39–16589; AD 2011–03–05] 

RIN 2120–AA64 

Airworthiness Directives; Dornier 

Luftfahrt GmbH Models Dornier 228– 

100, Dornier 228–101, Dornier 228–200, 

Dornier 228–201, Dornier 228–202, and 

Dornier 228–212 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued 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 TC Holder received from operators, 

whose fleets are operated in demanding 

operating-conditions and with very frequent 

Short Take-Off and Landing (STOL) 

operations, reports of cracks located in the 

web of fuselage frame 19. On 05 February 

2007, EASA issued Airworthiness Directive 

(AD) 2007–0028 which mandated Alert 

Service Bulletin (ASB) 228–266 and required 

an inspection of the frame 19 on all Dornier 

228 aeroplanes. In addition, the TC Holder 

also initiated a flight-test campaign including 

strain measurements as well as finite element 

modelling and fatigue analyses to better 

understand the stress distribution onto the 

frame 19 and the associated structural 

components. 

The results of these investigations 

confirmed that STOL operations diminish 

extensively the fatigue life of the frame 19. 

Fuselage frame 19 supports the rear 

attachment of the Main Landing Gear (MLG). 

This condition, if not corrected, could cause 

rupture of frame 19, leading to subsequent 

collapse of a MLG. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

March 14, 2011. 

On March 14, 2011, the Director of the 

Federal Register approved the 

incorporation by reference of Dornier 

228 Time Limits/Maintenance Checks 

Manual, Temporary Revision No. 05–27, 

dated August 4, 2008, listed in this AD. 

As of June 26, 2007 (72 FR 28591, 

May 22, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of RUAG 

Alert Service Bulletin No. ASB–228– 

266, dated December 1, 2006, listed in 

this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket 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 service information identified in 

this AD, contact RUAG Aerospace 

Services GmbH, Dornier 228 Customer 

Support, P.O. Box 1253, 82231 

Wessling, Germany; telephone: + 49 (0) 

8153–302280; fax: + 49 (0) 8153– 

303030. 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. 

FOR FURTHER INFORMATION CONTACT: Greg 

Davison, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on November 18, 2010 (75 FR 

70623), and proposed to supersede AD 

2007–11–03, Amendment 39–15060 (72 

FR 28591; May 22, 2007). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states that: 

The TC Holder received from operators, 

whose fleets are operated in demanding 

operating-conditions and with very frequent 

Short Take-Off and Landing (STOL) 

operations, reports of cracks located in the 

web of fuselage frame 19. On 05 February 

2007, EASA issued Airworthiness Directive 

(AD) 2007–0028 which mandated Alert 

Service Bulletin (ASB) 228–266 and required 

an inspection of the frame 19 on all Dornier 

228 aeroplanes. In addition, the TC Holder 

also initiated a flight-test campaign including 

strain measurements as well as finite element 

modelling and fatigue analyses to better 

understand the stress distribution onto the 

frame 19 and the associated structural 

components. 

The results of these investigations 

confirmed that STOL operations diminish 

extensively the fatigue life of the frame 19. 

Fuselage frame 19 supports the rear 

attachment of the Main Landing Gear (MLG). 

This condition, if not corrected, could cause 

rupture of frame 19, leading to subsequent 

collapse of a MLG. 

For the reasons described above, this new 

AD requires installation of reinforcements 

and butt straps on frame 19 at the lower part 

of the fuselage for aeroplanes used in 

operations where this frame may be subject 

to high stress and recurring inspections of 

that frame for all aeroplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a Note within the AD. 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1
6524 Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD will affect 

17 products of U.S. registry. We also 

estimate that it will take about 6 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $8,670 or $510 per product. 

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 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 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 the NPRM, 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. 

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 

removing Amendment 39–15060 (72 FR 

28591; May 22, 2007) and adding the 

following new AD: 

2011–03–05 Dornier Luftfahrt GmbH: 

Amendment 39–16589; Docket No. 

FAA–2010–1152; Directorate Identifier 

2009–CE–026–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective March 14, 2011. 

Affected ADs 

(b) This AD supersedes AD 2007–11–03, 

Amendment 39–15060. 

Applicability 

(c) This AD applies to Dornier Luftfahrt 

GmbH Model Dornier 228–100, Dornier 228– 

101, Dornier 228–200, Dornier 228–201, 

Dornier 228–202, and Dornier 228–212 

airplanes, all serial numbers, that are 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 53: Fuselage. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

The TC Holder received from operators, 

whose fleets are operated in demanding 

operating-conditions and with very frequent 

Short Take-Off and Landing (STOL) 

operations, reports of cracks located in the 

web of fuselage frame 19. On 05 February 

2007, EASA issued Airworthiness Directive 

(AD) 2007–0028 which mandated Alert 

Service Bulletin (ASB) 228–266 and required 

an inspection of the frame 19 on all Dornier 

228 aeroplanes. In addition, the TC Holder 

also initiated a flight-test campaign including 

strain measurements as well as finite element 

modelling and fatigue analyses to better 

understand the stress distribution onto the 

frame 19 and the associated structural 

components. 

The results of these investigations 

confirmed that STOL operations diminish 

extensively the fatigue life of the frame 19. 

Fuselage frame 19 supports the rear 

attachment of the Main Landing Gear (MLG). 

This condition, if not corrected, could cause 

rupture of frame 19, leading to subsequent 

collapse of a MLG. 

For the reasons described above, this new 

AD requires installation of reinforcements 

and butt straps on frame 19 at the lower part 

of the fuselage for aeroplanes used in 

operations where this frame may be subject 

to high stress and recurring inspections of 

that frame for all aeroplanes. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) For all airplanes, within 25 hours timein-service (TIS) after June 26, 2007 (the 

effective date of AD 2007–11–03), visually 

inspect the affected fuselage frame 19 using 

the instructions in Dornier 228 RUAG Alert 

Service Bulletin No. ASB–228–266, dated 

December 1, 2006. 

(2) If any crack is found during the 

inspection required in paragraph (f)(1) of this 

AD, before further flight, contact RUAG 

Aerospace Services GmbH, Dornier 228 

Customer Support, P.O. Box 1253, 82231 

Wessling, Germany; telephone: +49–(0)8153– 

30–2280; fax: +49–(0)8153–30–3030; e-mail: 

customersupport.dornier228@ruag.com for 

FAA-approved repair instructions and 

incorporate the repair on the airplane. 

(3) After accomplishment of paragraph 

(f)(1) or (f)(2) of this AD, as applicable, 

repetitively thereafter do Structural 

Significant Item (SSI) Task No. 53.37 of 

Structure Inspection Program of Dornier 228 

Time Limits/Maintenance Checks Manual, 

Temporary Revision No. 05–27, dated August 

4, 2008, at intervals not to exceed 2,400 

landings or 72 months, whichever occurs 

first. 

(g) If the number of landings is unknown, 

calculate the compliance times of landings in 

this AD by using hours TIS. Multiply the 

number of hours TIS by 0.8 to come up with 

the number of landings. For the purpose of 

this AD: 

(1) 800 landings equals 1,000 hours TIS; 

and 

(2) 1,600 landings equals 2,000 hours TIS. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: 

(1) The MCAI requires different 

compliance times for airplanes operated in 

different conditions. The FAA is not able to 

enforce compliance times based on airplane 

operations since there is no way of 

determining the amount of operations in 

different conditions. To ensure the unsafe 

condition is addressed adequately and 

timely, we are requiring the inspection for all 

airplanes following a guideline combining 

number of landings and life limits. 


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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules and Regulations 6525 

(2) The service information allows flight 

with known cracks provided they do not 

exceed a certain limit. FAA policy does not 

allow flight with cracks in primary structure. 

Since the fuselage is considered primary 

structure, we are mandating repair before 

further flight after any crack is found. 

Other FAA AD Provisions 

(h) 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: Greg Davison, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 329– 

4090. Before using any approved AMOC on 

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. 

(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. 

Related Information 

(i) Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2009–0085, dated 

April 14, 2009; RUAG Alert Service Bulletin 

No. ASB–228–266, dated December 1, 2006; 

and Dornier 228 Time Limits/Maintenance 

Checks Manual, Temporary Revision No. 05– 

27, dated August 4, 2008, for related 

information. For service information related 

to this AD, contact RUAG Aerospace Services 

GmbH, Dornier 228 Customer Support, P.O. 

Box 1253, 82231 Wessling, Germany; 

telephone: + 49 (0) 8153–302280; fax: + 49 

(0) 8153–303030. 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. 

Material Incorporated by Reference 

(h) You must use RUAG Alert Service 

Bulletin No. ASB–228–266, dated December 

1, 2006; and Dornier 228 Time Limits/ 

Maintenance Checks Manual, Temporary 

Revision No. 05–27, dated August 4, 2008, 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 

Dornier 228 Time Limits/Maintenance 

Checks Manual, Temporary Revision No. 05– 

27, dated August 4, 2008, under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) On June 26, 2007 (72 FR 28591, May 

22, 2007), the Director of the Federal Register 

previously approved the incorporation by 

reference of RUAG Alert Service Bulletin No. 

ASB–228–266, dated December 1, 2006. 

(3) For service information identified in 

this AD, contact RUAG Aerospace Services 

GmbH, Dornier 228 Customer Support, P.O. 

Box 1253, 82231 Wessling, Germany; 

telephone: + 49 (0) 8153–302280; fax: + 49 

(0) 8153–303030. 

(4) 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. 

(5) 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. 

Issued in Kansas City, Missouri, on January 

25, 2011. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–2006 Filed 2–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1186; Directorate 

Identifier 2009–CE–065–AD; Amendment 

39–16588; AD 2011–03–04] 

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. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. AD 2009–09– 

09 currently requires repetitive 

inspections of the rudder hinges and the 

rudder hinge brackets for damage, i.e., 

cracking, deformation, and 

discoloration. If damage is found during 

any inspection, AD 2009–09–09 also 

requires replacing the damaged rudder 

hinge and/or rudder hinge bracket. This 

new AD retains the inspection 

requirements of AD 2009–09–09, adds 

airplanes to the Applicability section, 

and adds a terminating action for the 

repetitive inspection requirements. This 

AD resulted from the manufacturer 

developing a modification that 

terminates the repetitive inspections 

and from the manufacture adding 

airplane serial numbers into the 

Applicability section. 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 is effective March 14, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of March 14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 11, 2009 (74 FR 19873, April 

30, 2009). 

ADDRESSES: 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. 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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 


wwoods2 on DSK1DXX6B1PROD with RULES_PART 1