77376 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

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: 

2011–25–01 Apical Industries, Inc.: Docket 

No. FAA–2010–1190; Directorate 

Identifier 2010–SW–038–AD. 

Applicability: The helicopter models, 

certificated in any category, with an 

Emergency Float Kit with a part number (P/ 

N) and serial number (S/N), installed by a 

supplemental type certificate (STC), as 

follows: 

Kit P/N Kit S/N Affected helicopter model STC No. 

614.3001 .................................. 080 and below ......................... Bell Helicopter Textron (Bell) 407 ............................................. SR01535LA 

614.3003 .................................. 133 and below ......................... Bell 206L, L–1, L–3, and L–4 ................................................... SR01535LA 

614.3007 .................................. 014 and below ......................... Bell 206A and B ........................................................................ SR01535LA 

614.7601 .................................. 045 and below ......................... Bell 210, 212, 412, 412CF, 412EP, AB412, and AB412EP ..... SR01779LA 

634.2901 .................................. 012 and below ......................... Bell 427 ..................................................................................... SR01813LA 

644.1801 .................................. 031 and below ......................... Eurocopter Deutschland Gmbh (Eurocopter) EC135 ............... SR01855LA 

20430–300 ............................... 009 and below ......................... Eurocopter BO–105A, C, S, LS A–1 and LS A–3 .................... SR00856LA 

Compliance: Within 180 days, unless 

accomplished previously. 

To install placards to aid in locating and 

deploying liferafts to prevent further injury 

or loss of life in the event of a helicopter 

landing in the water, do the following: 

(a) Install the Liferaft External Inflation 

Handle Placard, P/N 600.0897, shown in 

Figure 1 of Apical Industries Inc. Alert 

Service Bulletin SB2008–01, Revision A, 

dated March 3, 2010 (ASB), on the crosstubes 

or fuselage near the external T-Handles, as 

shown for two model helicopters in Figures 

2 and 3, by following the Accomplishment 

Instructions, 1.0, paragraphs 1 through 5, of 

the ASB. 

(b) Remove the Liferaft Operation Placard, 

P/N 634.9703, Revision N/C through B, as 

shown in Figure 4 of the ASB, and install 

Liferaft Operation Placard, P/N 634.9703, 

Revision C, as shown in Figure 5, above all 

aircraft exits, inside the aircraft in plain 

view. 

(c) 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, Los Angeles 

Aircraft Certification Office, FAA, ATTN: 

Venessa Stiger, Aviation Safety Engineer, 

3960 Paramount Blvd., Lakewood, California 

90712–4137, telephone (562) 627–5337, fax 

(562) 627–5210, for information about 

previously approved alternative methods of 

compliance. 

(d) The Joint Aircraft System/Component 

(JASC) Codes are 2564: Liferaft and 3212: 

Emergency Flotation Section. 

(e) The modification shall be done in 

accordance with the specified portions of 

Apical Industries Inc. Alert Service Bulletin 

SB2008–01, Revision A, dated March 3, 2010. 

The Director of the Federal Register approved 

this incorporation by reference in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Copies may be obtained from Apical 

Industries, Inc., 2608 Temple Heights Drive, 

Oceanside, California 92056–3512, telephone 

(760) 724–5300, fax (760) 758–9612, http:// 

www.apicalindustries.com/. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Fort Worth, Texas 76137 or 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. 

(f) This amendment becomes effective on 

January 17, 2012. 

Issued in Fort Worth, Texas, on November 

18, 2011. 

Lance T. Gant, 

Acting Manger, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–30925 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0911; Directorate 

Identifier 2010–NM–248–AD; Amendment 

39–16883; AD 2011–25–07] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all BAE 

Systems (Operations) Limited Model 

4101 airplanes. This 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: 

A door failure mode has been reported by 

an operator. 

Investigation has shown that the 

passenger/crew entry door pin-guide plates 

can fail prior to the expected fatigue life. A 

metallurgical examination of the failed 

component (lower guide plate) concluded 

that the occurred failure was due to 

exfoliation corrosion. 

The current inspection regime is not 

adequate to identify early stages of this 

corrosion. 

This condition, if not corrected, can lead 

to the sudden depressurisation of the 

aeroplane and consequently may injure the 

occupants. 

* * * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

January 17, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 17, 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1175; 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 August 31, 2011 (76 FR 

54139). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A door failure mode has been reported by 

an operator. 

Investigation has shown that the 

passenger/crew entry door pin-guide plates 

can fail prior to the expected fatigue life. A 

metallurgical examination of the failed 

component (lower guide plate) concluded 


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Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 77377 

that the occurred failure was due to 

exfoliation corrosion. 

The current inspection regime is not 

adequate to identify early stages of this 

corrosion. 

This condition, if not corrected, can lead 

to the sudden depressurisation of the 

aeroplane and consequently may injure the 

occupants. 

For the reasons described above, this 

[EASA] AD requires immediate and periodic 

ultrasonic inspections [for a split caused by 

exfoliation corrosion] of the door pin guides 

and the accomplishment of the relevant 

corrective actions [replacing the affected 

guideplates] as necessary. 

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 54139, August 31, 2011) 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 our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 2 

products of U.S. registry. We also 

estimate that it will take about 2 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

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

be $340, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $525 for a cost of $695 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 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 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 

54139, August 31, 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: 

2011–25–07 BAE Systems (Operations) 

Limited: Amendment 39–16883. Docket 

No. FAA–2011–0911; Directorate 

Identifier 2010–NM–248–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective January 17, 2012. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all BAE Systems 

(Operations) Limited Model 4101 airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

A door failure mode has been reported by 

an operator. 

Investigation has shown that the 

passenger/crew entry door pin-guide plates 

can fail prior to the expected fatigue life. A 

metallurgical examination of the failed 

component (lower guide plate) concluded 

that the occurred failure was due to 

exfoliation corrosion. 

The current inspection regime is not 

adequate to identify early stages of this 

corrosion. 

This condition, if not corrected, can lead 

to the sudden depressurisation of the 

aeroplane and consequently may injure the 

occupants. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Actions 

(g) Within 6 months after the effective date 

of this AD, do an ultrasonic inspection of the 

passenger/crew door upper and lower guide 


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77378 Federal Register / Vol. 76, No. 239 / Tuesday, December 13, 2011 / Rules and Regulations 

plates for a split caused by exfoliation 

corrosion, in accordance with the 

Accomplishment Instructions of BAE 

SYSTEMS (Operations) Limited Service 

Bulletin J41–52–064, dated September 15, 

2009. Repeat the ultrasonic inspection, 

thereafter, at intervals not to exceed 48 

months. 

(h) If a split caused by exfoliation corrosion 

of an area of 78mm2 (0.12 in.2) or greater is 

found during any ultrasonic inspection 

required by paragraph (g) of this AD: Before 

further flight, replace any affected guide 

plates with a serviceable guide plate, in 

accordance with the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Service Bulletin J41–52–064, dated 

September 15, 2009. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(i) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1175; 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. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0179, 

dated August 30, 2010; and BAE Systems 

(Operations) Limited Service Bulletin J41– 

52–064, dated September 15, 2009; for 

related information. 

Material Incorporated by Reference 

(k) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information on the date 

specified: 

(1) BAE Systems (Operations) Limited 

Service Bulletin J41–52–064, dated 

September 15, 2009, approved for IBR 

January 17, 2012. 

(2) For BAE Systems (Operations) Limited 

service information identified in this AD, 

contact Customer Information Department, 

Prestwick International Airport, Ayrshire, 

KA9 2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 1292 

675704; email 

RApublications@baesystems.com; Internet 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/index.htm. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at an NARA facility, call (202) 741– 

6030, or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

November 23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–31314 Filed 12–12–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0710; Directorate 

Identifier 2010–NE–26–AD; Amendment 

39–16892; AD 2011–26–02] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 1 Series Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising an existing 

airworthiness directive (AD) for the 

products listed above. This AD was 

prompted by Turbomeca restoring all or 

part of the life limits of the affected 

discs, and European Aviation Safety 

Agency’s (EASA) issuance of AD 2010– 

0101R2, dated March 24, 2011, to do the 

same. Turbomeca has introduced a 

reinforced eddy-current inspection (ECI) 

which, combined with a revised 

analysis, allows the life limit of the 

affected discs to be extended. We are 

issuing this revision to prevent failure of 

the gas generator (GG) second stage 

turbine disc which could result in the 

release of high energy debris and 

damage to the helicopter. 

DATES: This AD is effective January 17, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca, 40220 Tarnos, France; 

phone: 33 05 59 74 40 00; fax: 33 05 59 

74 45 15; email: noriadallas@turbomeca.com. You may 

review copies of the referenced service 

information at the FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA. For 

information on the availability of this 

material at the FAA, call (781) 238– 

7125. 

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 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Frederick Zink, Aerospace Engineer, 

Engine Certification Office, FAA, 12 

New England Executive Park, 

Burlington, MA; phone: (781) 238–7779; 

fax: (781) 238–7199; email: 

frederick.zink@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to revise AD 2010–19–06, 

amendment 39–16434 (75 FR 57371, 

September 21, 2010). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

July 19, 2011 (76 FR 42610). That NPRM 

proposed to require removing GG 

second stage turbine discs, P/N 0 292 25 

040 0, that do not have the ‘‘CFR’’ 

marking, from service before exceeding 

4,000 cycles-in-service (CIS) since-new. 

That NPRM also proposed to require 

removing GG second stage turbine discs, 

P/N 0 292 25 040 0, that have the ‘‘CFR’’ 

marking, from service before exceeding 

6,500 CIS since-new. 

That NPRM was prompted by 

Turbomeca restoring all or part of the 

life limits of the affected discs, per 


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