Federal Register / Vol. 78, No. 84 / Wednesday, May 1, 2013 / Rules and Regulations 25367 

2013–08–19 Eurocopter France Helicopters:

Amendment 39–17437; Docket No. 

FAA–2009–0951; Directorate Identifier 

2007–SW–52–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS350B, BA, B1, B2, B3, 

C, D, D1, AS355E, F, F1, F2, and N 

helicopters, with sliding door premodification (MOD) 073298 or pre-MOD 

073308, installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the rear roller support shaft (shaft) 

or the rear fitting (fitting) of the sliding door. 

This condition could result in loss of the 

sliding door, which could come into contact 

with the rotor system, leading to damage to 

the helicopter and loss of helicopter control. 

(c) Effective Date 

This AD becomes effective June 5, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

(1) For a sliding door with less than 90 

hours time-in-service (TIS), on or before 

accumulating a total of 110 hours TIS, 

conduct the visual and dye penetrant 

inspections of the shaft and the fitting of the 

sliding door for a crack by reference to Figure 

1 and by following the Operational 

Procedure, paragraph 2.B.1 and 2.B.2, of 

Eurocopter Alert Service Bulletin (ASB) No. 

05.00.47 dated July 19, 2006, for the Model 

AS350 helicopters (ASB 05.00.47) or ASB 

No. 05.00.45 dated July 19, 2006, for the 

Model AS355 helicopters (ASB 05.00.45), 

except you are not required to contact the 

manufacturer. 

(i) If no crack is found in the shaft or 

fitting, reinstall the shaft on the fitting, fit the 

spring pins, and plug the pin holes by 

following the Operational Procedure, 

paragraph 2.B.2. of ASB 05.00.47 or 05.00.45, 

whichever is appropriate for your model 

helicopter. 

(ii) If you find a crack in the fitting, replace 

the fitting with an airworthy fitting before 

further flight. 

(iii) If you find a crack in the shaft, replace 

the shaft with an airworthy shaft before 

further flight by reference to Figure 1 and by 

following paragraph 2.B.3. of ASB 05.00.47 

or 05.00.45, whichever is appropriate for 

your model helicopter. 

(2) For a sliding door with 90 or more 

hours TIS, within the next 20 hours TIS, and 

thereafter at intervals not to exceed 110 hours 

TIS, conduct the visual and dye penetrant 

inspections of the shaft and the fitting of the 

sliding door for a crack by reference to Figure 

1 and by following the Operational 

Procedure, paragraph 2.B.1 and 2.B.2, of ASB 

05.00.47 or ASB 05.00.45, whichever is 

appropriate for your model helicopter, except 

you are not required to contact the 

manufacturer. 

(i) If no crack is found in the shaft and 

fitting, reinstall the shaft or fitting, fit the 

spring pins, and plug the pin holes by 

following the Operational Procedure, 

paragraph 2.B.2. of ASB 05.00.47 or 05.00.45, 

whichever is appropriate for your model 

helicopter. 

(ii) If you find a crack in the fitting, replace 

the fitting with an airworthy fitting before 

further flight. 

(iii) If you find a crack in the shaft, replace 

the shaft with an airworthy shaft before 

further flight by reference to Figure 1 and by 

following paragraph 2.B.3. of ASB 05.00.47 

or 05.45, whichever is appropriate for your 

model helicopter. 

(3) After the effective date of this AD, do 

not install any of the following parts on any 

helicopter: 

(i) Left-hand sliding door, part number (P/ 

N) 350A25–0030–00XX, 350A25–0120– 

00XX, and 350AMR–0227–0052; 

(ii) Right-hand sliding door, P/N 350A25– 

0030–01XX, 350A25–0120–01XX, 350A25– 

0120–03XX, and 350AMR–0227–0051; 

(iii) Rail roller pin, P/N 350A25–1275–20; 

and 

(iv) Cast roller support fittings, P/N 

350A25–1270–20 and P/N 350A25–1270–22. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2007–0236, dated August 31, 2007. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5344, Fuselage Door Hinges. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise: 

(i) Eurocopter France Alert Service Bulletin 

No. 05.00.47, Revision 0, dated July 19, 2006. 

(ii) Eurocopter France Alert Service 

Bulletin No. 05.00.45, Revision 0, dated July 

19, 2006. 

(3) For Eurocopter France service 

information identified in this AD, contact 

American Eurocopter Corporation, 2701 N. 

Forum Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232–0323; 

fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on April 12, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09436 Filed 4–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0631; Directorate 

Identifier 2011–SW–021–AD; Amendment 

39–17282; AD 2012–25–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter France Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350B3, AS350C, AS350D, AS350D1, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters with 

certain Aerazur emergency flotation gear 

attachment brackets (brackets) installed. 

This AD requires an initial and 

recurring inspection of the brackets for 

a crack, and if there is a crack, replacing 

the cracked bracket with an airworthy 

bracket. This AD was prompted by 

reports of cracks on the brackets. The 

actions of this AD are intended to 

prevent failure of the emergency 

flotation system and loss of float 

stability in the event of a water landing. 

DATES: This AD is effective June 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of June 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 


wreier-aviles on DSK5TPTVN1PROD with RULES
25368 Federal Register / Vol. 78, No. 84 / Wednesday, May 1, 2013 / Rules and Regulations 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http:// 

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 18, 2012, at 77 FR 36216, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Eurocopter France Model AS350B, 

AS350BA, AS350B1, AS350B2, 

AS350B3, AS350C, AS350D, AS350D1, 

AS355E, AS355F, AS355F1, AS355F2, 

AS355N, and AS355NP helicopters with 

a bracket, part number (P/N) 158172, 

158173, 158288, or 158289, installed. 

That NPRM proposed to require an 

initial and recurring inspection of the 

brackets for a crack, and if there was a 

crack, replacing the cracked bracket 

with an airworthy bracket. The 

proposed requirements were intended to 

prevent failure of the emergency 

flotation system and loss of float 

stability in the event of a water landing. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2011–0072, 

dated April 20, 2011 (AD 2011–0072), to 

correct an unsafe condition for the 

Eurocopter AS350B, AS350BA, 

AS350BB, AS350B1, AS350B2, 

AS350B3, AS350D, AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and 

AS355NP helicopters with Aerazur 

emergency flotation gear attachments 

installed. EASA stated it received 

several reports of cracks being found on 

the brackets which appear to be caused 

by stress corrosion. This condition, if 

not corrected, could result in ‘‘rupture 

of the emergency flotation gear 

attachment brackets’’ during a water 

landing. The helicopter’s float stability 

could no longer be ensured, possibly 

resulting in damage to the helicopter 

and injury to the occupants. EASA’s AD 

requires an initial inspection of the 

brackets, replacement of any brackets 

found with cracks, and re-inspection of 

the brackets every 13 months. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(77 FR 36216, June 18, 2012). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed except we are incorporating a 

figure by reference instead of including 

it in our AD to meet current publication 

requirements. This change is consistent 

with the intent of the proposals in the 

NPRM (77 FR 36216, June 18, 2012) and 

will not increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Interim Action 

We consider this AD interim action. 

Eurocopter is developing a modification 

that will address the unsafe condition 

identified in this AD. Once this 

modification is developed, approved, 

and available, we might consider 

additional rulemaking. 

Differences Between This AD and the 

EASA AD 

Differences between this AD and the 

EASA AD include: 

• The EASA AD applies to 

Eurocopter Model AS 350 BB 

helicopters. This AD does not as this 

model is not type certificated by the 

FAA. Additionally, the EASA AD 

excludes Eurocopter Models AS350C 

and AS350D1, whereas this AD includes 

them. 

• The EASA AD mandates different 

compliance times depending on the 

manufacture date of the helicopter. We 

mandate inspecting all helicopters 

within 110 hours TIS or 3 months, 

whichever occurs first, regardless of 

date of manufacture. 

• This AD does not require returning 

cracked brackets to the manufacturer. 

Related Service Information 

Eurocopter issued Alert Service 

Bulletin (ASB) No. AS350–05.00.63, 

Revision 1, dated April 18, 2011, and 

ASB No. AS355–05.00.58, Revision 1, 

dated April 18, 2011. These ASBs 

specify procedures to inspect the front 

and rear brackets at regular intervals. 

EASA classified these ASBs as 

mandatory and issued EASA AD 2011– 

0072 to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

733 helicopters of U.S. Registry and that 

labor rates will average $85 an hour. 

Inspecting the brackets will take about 

4 work-hours per inspection cycle for a 

labor cost of $340 per helicopter and 

$249,220 for the U.S. fleet. Replacing 

the bracket, if needed, will require about 

1 work-hour and about $1,130 for the 

parts. Thus, the total cost to replace one 

bracket will be about $1,215. 

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 

helicopters identified in this rulemaking 

action. 

Regulatory Findings 

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 


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Federal Register / Vol. 78, No. 84 / Wednesday, May 1, 2013 / Rules and Regulations 25369 

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); 

(3) Will not affect intrastate aviation 

in Alaska to the extent that it justifies 

making a regulatory distinction; 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 an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2012–25–01 Eurocopter France: 

Amendment 39–17282; Docket No. 

FAA–2012–0631; Directorate Identifier 

2011–SW–021–AD. 

(a) Applicability 

This AD applies to Eurocopter France 

Model AS350B, AS350BA, AS350B1, 

AS350B2, AS350B3, AS350C, AS350D, 

AS350D1, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, and AS355NP helicopters 

with an Aerazur emergency flotation gear 

attachment bracket, part number 158172, 

158173, 158288, or 158289, installed, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in an attachment bracket of the 

emergency flotation gear. This condition 

could result in failure of the emergency 

flotation system and loss of float stability in 

the event of a water landing. 

(c) Effective Date 

This AD becomes effective June 5, 2013. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless 

accomplished previously. 

(e) Required Actions 

Within 110 hours time-in-service or 3 

months, whichever occurs first, and 

thereafter at intervals not to exceed 13 

months: 

(1) Using a 5X or higher power magnifying 

glass, visually inspect the front emergency 

floatation gear attachment bracket, section B– 

B, item (e) in Areas F, G, and H of Figure 1 

of Eurocopter Alert Service Bulletin No. 

AS350–05.00.63 or No. AS355–05.00.58, both 

Revision 1, and both dated April 18, 2011, as 

applicable to your model helicopter (ASB); 

and the rear emergency flotation gear 

attachment bracket, section A–A, item (a) in 

Areas D and E of Figure 1 of the ASB, for a 

crack. 

(2) If there is a crack, replace the cracked 

emergency floatation gear attachment bracket 

with an airworthy emergency floatation gear 

attachment bracket prior to reinstallation of 

the emergency flotation equipment. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0072, dated April 20, 2011. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2560, Emergency Equipment. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin (ASB) 

No. AS350–05.00.63, Revision 1, dated April 

18, 2011. 

(ii) Eurocopter ASB No. AS355–05.00.58, 

Revision 1, dated April 18, 2011. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, Texas 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on April 12, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–09437 Filed 4–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0936; Directorate 

Identifier 2011–NM–269–AD; Amendment 

39–17433; AD 2013–08–16] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–700 

and –700C series airplanes. This AD 

was prompted by reports of early fatigue 

cracks at chem-mill areas on the crown 

skin panels. This AD requires repetitive 

inspections for cracking of the fuselage 

skin at certain locations at chem-mill 

areas, and repair if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the skin panel at the 

specified chem-mill step locations, 

which could result in rapid 

decompression of the airplane. 

DATES: This AD is effective June 5, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 


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