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

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Rules and Regulations Federal Register

12989 

Vol. 77, No. 43 

Monday, March 5, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0997; Directorate 

Identifier 2011–NM–043–AD; Amendment 

39–16963; AD 2012–04–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A330–200 series 

airplanes; Model A330–300 series 

airplanes; Model A340–200 series 

airplanes; and Model A340–300 series 

airplanes. This AD was prompted by a 

report that three failures of the 

retraction bracket occurred during 

fatigue testing before the calculated life 

limit of the main landing gear (MLG). 

This AD requires repetitive replacement 

of the affected retraction bracket of the 

MLG. We are issuing this AD to prevent 

failure of the retraction bracket, which 

could result in a MLG extension with no 

damping, and consequent structural 

damage of the MLG. 

DATES: This AD becomes effective April 

9, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

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 October 5, 2011 (76 FR 

61645). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During fatigue testing of the MLG [main 

landing gear], three failures of the retraction 

bracket occurred before the calculated life 

limitation. Further analysis has confirmed 

that those failures were due to fatigue 

initiated by fretting between the bush and lug 

bore. 

The failure of the retraction bracket, if not 

detected, could lead to a MLG extension with 

no damping resulting in MLG structural 

damage. 

Airbus carried out an investigation, 

demonstrating that the life limit of retraction 

brackets must be reduced to 19,800 Landings 

(LDG), which is below the life limit stated in 

the following A330 and A340 Airbus ALS 

Part 4 revisions: 

—Airbus A330 ALS Part 4 revision 02 

approved by EASA on 16 December 2009. 

—Airbus A340 ALS Part 4 revision 01 

approved by EASA on 15 December 2009. 

In order to maintain the structural integrity 

of the aeroplane, this [EASA] AD requires the 

replacement of these MLG retraction brackets 

before the accumulation of 19,800 total LDG. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 61645, October 5, 2011) or on the 

determination of the cost to the public. 

Explanation of Change Made to This 

AD 

We have re-designated Notes 1 and 2 

of the NPRM (76 FR 61645, October 5, 

2011) as paragraph (h) in this final rule, 

and re-identified subsequent paragraphs 

accordingly. 

Conclusion 

We reviewed the relevant data, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

61645, October 5, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 61645, 

October 5, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD will affect 

29 products of U.S. registry. We also 

estimate that it will take about 25 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 $200,000 

per product. Based on these figures, we 

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

operators to be $5,861,625, or $202,125 

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. 


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12990 Federal Register / Vol. 77, No. 43 / Monday, March 5, 2012 / Rules and Regulations 

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. 

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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains the NPRM (76 FR 61645, 

October 5, 2011), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations 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 adding 

the following new AD: 

2012–04–07 Airbus: Amendment 39–16963. 

Docket No. FAA–2011–0997; Directorate 

Identifier 2011–NM–043–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 9, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

201, –202, –203, –223, –243, –301, –302, 

–303, –321, –322, –323, –341, –342, and –343 

airplanes; and Model A340–211, –212, –213, 

–311, –312, and –313 airplanes; certificated 

in any category, all manufacturer serial 

numbers; except airplanes on which Airbus 

modification 54500 has been embodied in 

production; and except airplanes on which 

Airbus Service Bulletin A330–32–3212 or 

Airbus Service Bulletin A340–32–4256 has 

been embodied in service; as applicable to 

airplane model. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by a report that 

three failures of the retraction bracket 

occurred during fatigue testing before the 

calculated life limit of the main landing gear 

(MLG). We are issuing this AD to prevent 

failure of the retraction bracket, which could 

result in a MLG extension with no damping, 

and consequent structural damage of the 

MLG. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Replacement 

Before the accumulation of 19,800 total 

landings on the retraction brackets of the 

MLG or within 900 flight hours after the 

effective date of this AD, whichever occurs 

later: Replace the affected retraction bracket 

of the MLG specified in table 1 of this AD 

with a serviceable part, in accordance with 

a method approved by the Manager, 

International Branch, ANM–116, FAA, or 

European Aviation Safety Agency (EASA) (or 

its delegated agent). Thereafter, before the 

accumulation of 19,800 total landings on any 

retraction bracket of the MLG identified in 

table 1 of this AD, replace the retraction 

bracket with a serviceable part, in accordance 

with a method approved by the Manager, 

International Branch, ANM–116, FAA, or 

EASA (or its delegated 

TABLE 1—RETRACTION BRACKET OF

THE MLG 

Nomenclature Part No. 

Retraction Bracket of the 

MLG .................................. 201478303 

201478304 

201478305 

201478306 

201478307 

201478308 

201428380 

201428381 

201428382 

201428383 

201428384 

201428385 

201428378 

201428379 

201428351 

201428352 

Note 1 to paragraph (g) of this AD: 

Additional guidance for the replacement can 

be found in Task 32–11–11–000–804–A, 

Removal of the MLG Retraction Bracket 

Assembly, and Task 32–11–11–400–804–A, 

Installation of the MLG Retraction Bracket 

Assembly, of Subsection 32–11–11 of 

Chapter 32 of the Airbus A330 or A340 

Aircraft Maintenance Manual, as applicable. 

(h) Definitions 

(1) For purposes of this AD, ‘‘total 

landings’’ is defined as the accumulated 

landings since the initial entry of the MLG 

retraction bracket into service on any 

airplane. 

(2) For purposes of this AD, the initial 

entry into service for the transferable systems 

components/items is defined as the date at 

which the component/item accomplishes the 

first flight for which it will undertake its 

intended function. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(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. 

(j) Related Information 

(1) Refer to MCAI Airworthiness Directive 

EASA AD 2010–0205, dated October 8, 2010, 

for related information. 

(2) For Airbus service information 

identified in this AD contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330– 

A340@airbus.com; Internet http:// 

www.airbus.com. 

(k) Material Incorporated by Reference 

None. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 43 / Monday, March 5, 2012 / Rules and Regulations 12991 

Issued in Renton, Washington, on February 

14, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–4498 Filed 3–2–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1420; Directorate 

Identifier 2011–CE–035–AD; Amendment 

39–16905; AD 2011–27–04] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Airplanes 

Equipped With a Certain Supplemental 

Type Certificate (STC) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to all Hawker Beechcraft 

Corporation Models 95–C55, D55, E55, 

58, and 58A airplanes equipped with a 

certain STC. The description of the 

affected STCs in the first sentence of the 

SUPPLEMENTARY INFORMATION, Discussion 

section, is incorrect. This document 

corrects that error. In all other respects, 

the original document remains the 

same. 

DATES: This final rule is effective March 

5, 2012. The effective date for AD 2011– 

27–04 (76 FR 81790, December 29, 

2011) remains December 29, 2011. 

ADDRESSES: 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 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Eric 

B. Potter, Aerospace Engineer, Atlanta 

Aircraft Certification Office, FAA, 1701 

Columbia Avenue, College Park, Georgia 

30337; phone: (404) 474–5583; fax: (404) 

474–5606; email: eric.potter@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2011–27–04, 

amendment 39–16905 (76 FR 81790, 

December 29, 2011), currently requires 

assuring the airspeed indicator(s) and/or 

airspeed limitations placard(s) have the 

correct minimum control speed (VMC) 

markings for all Hawker Beechcraft 

Corporation Models 95–C55, D55, E55, 

58, and 58A airplanes equipped with a 

certain STC. 

As published, the description of the 

affected STCs in the first sentence of the 

SUPPLEMENTARY INFORMATION, Discussion 

section, is incorrect. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the preamble to the final rule 

is being published in the Federal 

Register. 

The effective date of this AD remains 

December 29, 2011. 

Correction of Non-Regulatory Text 

In the Federal Register of December 

29, 2011, AD 2011–27–04; Amendment 

39–16905 is corrected as follows: 

On page 81790, in the third column, 

on line 2 under the heading 

SUPPLEMENTARY INFORMATION, 

Discussion, correct ‘‘, we found that 

STC SA1762SO (installation of vortex 

generators) and STC SA4016NM 

(Foxstar Baron modification of winglets 

and different engines and propellers) 

were installed.’’ to read ‘‘, we found that 

STC SA1762SO (Foxstar Baron 

modification of winglets and different 

engines and propellers) and STC 

SA4016NM (installation of vortex 

generators) were installed.’’ 

Issued in Kansas City, Missouri, on 

February 23, 2012. 

John Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–5290 Filed 3–2–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0588; Directorate 

Identifier 2010–SW–074–AD; Amendment 

39–16717; AD 2011–12–10] 

RIN 2120–AA64 

Airworthiness Directives; Robinson 

Helicopter Company Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that was 

published in the Federal Register. That 

AD applies to Robinson Helicopter 

Company (Robinson) Model R22, R22 

Alpha, R22 Beta, R22 Mariner, R44, and 

R44 II helicopters. The paragraph 

reference in paragraph (b) of the 

Compliance section is incorrect. 

Paragraph (b) references paragraph (d), 

when it should reference paragraph (c). 

This document corrects that error. 

Additionally, the word ‘‘inspection’’ has 

been added in paragraph (b) for 

clarification. In all other respects, the 

original document remains the same. 

DATES: The effective date of this final 

rule is March 5, 2012. The effective date 

for AD 2011–12–10 remains July 5, 

2011. 

Examining the AD Docket: You may 

examine the AD docket on the Internet 

at http://www.regulations.gov; or in 

person at the Docket Operations Office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Eric 

D. Schrieber, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

Transport Airplane Directorate, FAA, 

3960 Paramount Blvd., Lakewood, CA 

90712; telephone (562) 627–5348; email 

eric.schrieber@faa.gov (regarding Model 

R22 helicopters); or Fred Guerin, 

Aerospace Engineer, Los Angeles 

Aircraft Certification Office, Transport 

Airplane Directorate, FAA, 3960 

Paramount Blvd., Lakewood, CA 90712; 

telephone (562) 627–5232; email 

fred.guerin@faa.gov (regarding Model 

R44 helicopters). 

SUPPLEMENTARY INFORMATION: 

Airworthiness Directive 2011–12–10, 

Amendment 39–16717 (76 FR 35330, 

June 17, 2011), currently includes the 

following paragraph (b) in the 

compliance section: 

‘‘(b) If you find any bare metal in the 

area of the skin-to-spar bond line, before 

further flight, inspect the blade by 

following the requirements of paragraph 

(d) of this AD.’’ 

As published, the reference to 

paragraph (d) is incorrect. The correct 

reference is to paragraph (c). Paragraph 

(c) contains the inspection 

requirements, and the incorrect 


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