2366 Federal Register / Vol. 79, No. 9 / Tuesday, January 14, 2014 / Rules and Regulations 

The FAA issues special conditions, as 

defined in 14 CFR 11.19, under § 11.38, 

and they become part of the typecertification basis under § 21.17(a)(2). 

Novel or Unusual Design Features 

The Airbus Model A350–900 series 

will incorporate the following novel or 

unusual design features: An electronic 

flight control system that can affect how 

the airplane responds to a roll 

maneuver. This requires that the roll 

maneuver result from defined 

movements of the cockpit roll control as 

opposed to defined aileron deflections. 

This also requires an additional load 

condition at VA, in which the cockpit 

roll control is returned to neutral 

following the initial roll input. 

Discussion 

These proposed special conditions 

differ from similar special conditions 

applied on previous programs; and are 

limited to the roll axis only, whereas 

previous special conditions also 

included the pitch and yaw axes. 

Special conditions are no longer needed 

for the pitch or yaw axes, because 14 

CFR part 25 Amendment 25–91 takes 

into account the effects of an electronic 

flight control system in those axes 

(§ 25.331 for pitch and § 25.351 for 

yaw). 

Applicability 

As discussed above, these special 

conditions apply to Airbus Model 

A350–900 series airplanes. Should 

Airbus apply later for a change to the 

type certificate to include another 

model incorporating the same novel or 

unusual design feature, the special 

conditions would apply to that model as 

well. 

Conclusion 

This action affects only certain novel 

or unusual design features on the Airbus 

Model A350–900 series airplanes. It is 

not a rule of general applicability. 

The substance of these special 

conditions has been subjected to the 

notice and comment period in several 

prior instances and has been derived 

without substantive change from those 

previously issued. It is unlikely that 

prior public comment would result in a 

significant change from the substance 

contained herein. Therefore, the FAA 

has determined that prior public notice 

and comment are unnecessary and 

impracticable, and good cause exists for 

adopting these special conditions upon 

issuance. The FAA is requesting 

comments to allow interested persons to 

submit views that may not have been 

submitted in response to the prior 

opportunities for comment described 

above. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701, 

44702, 44704. 

The Special Conditions 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the following special 

conditions are issued as part of the type 

certification basis for Airbus Model 

A350–900 series airplanes. 

1. Design Roll Maneuver Conditions 

The following conditions, speeds, and 

cockpit roll control motions (except as 

the motions may be limited by pilot 

effort) must be considered in 

combination with an airplane load 

factor of zero and of two-thirds of the 

positive maneuvering factor used in 

design. In determining the resulting 

control surface deflections, the torsional 

flexibility of the wing must be 

considered in accordance with 

§ 25.301(b): 

a. Conditions corresponding to steady 

rolling velocities must be investigated. 

In addition, conditions corresponding to 

maximum angular acceleration must be 

investigated for airplanes with engines 

or other weight concentrations outboard 

of the fuselage. For the angular 

acceleration conditions, zero rolling 

velocity may be assumed in the absence 

of a rational time history investigation 

of the maneuver. 

b. At VA, sudden movement of the 

cockpit roll control up to the limit is 

assumed. The position of the cockpit 

roll control must be maintained until a 

steady roll rate is achieved and then 

must be returned suddenly to the 

neutral position. 

c. At VC, the cockpit roll control must 

be moved suddenly and maintained so 

as to achieve a roll rate not less than 

that obtained in paragraph b. 

d. At VD, the cockpit roll control must 

be moved suddenly and maintained so 

as to achieve a roll rate not less than 

one-third of that obtained in paragraph 

b. 

Issued in Renton, Washington, on October 

22, 2013. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–00451 Filed 1–13–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0635; Directorate 

Identifier 2012–SW–081–AD; Amendment 

39–17720; AD 2013–26–11] 

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 (Eurocopter) Model 

EC225LP helicopters. This AD requires 

inspecting the swashplates for corrosion 

or a crack, and making the appropriate 

repairs or replacement of parts. This AD 

was prompted by the discovery of 

corrosion on the swashplates when the 

main rotor hub (MRH) assemblies were 

reconditioned. The actions of this AD 

are intended to detect corrosion or a 

crack in the swashplates, which could 

lead to failure of the swashplates and 

subsequent loss of helicopter control. 

DATES: This AD is effective February 18, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 18, 2014. 

ADDRESSES: For 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. 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, the foreign 

authority’s AD, any incorporated-byreference 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 


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Federal Register / Vol. 79, No. 9 / Tuesday, January 14, 2014 / Rules and Regulations 2367 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 23, 2013, at 78 FR 44043, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Eurocopter Model EC225LP helicopters 

with an MRH assembly with a rotating 

swashplate, part number (P/N) 332A31– 

3074–00 or 332A31–3076–00, and 

stationary swashplate, P/N 332A31– 

3079–00 or 332A31–3079–01, installed. 

The NPRM proposed to require 

inspecting the swashplates for corrosion 

or a crack, and making the appropriate 

repairs or replacement of parts. The 

proposed requirements were intended to 

prevent failure of the swashplate and 

subsequent loss of helicopter control. 

The NPRM was prompted by AD No. 

2012–0131, dated July 31, 2012, issued 

by the European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for Eurocopter Model EC225LP 

helicopters. EASA advises that 

corrosion has been reported on the 

rotating and stationary swashplates of 

the MRH assembly of several 

helicopters. This condition may cause 

cracks on the swashplates, which may 

cause failure of MRH parts and loss of 

control of the helicopter. The EASA AD 

requires repetitive inspections of the 

affected swashplates after two years and 

replacing the MRH assembly if a crack 

is found. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(78 FR 44043, July 23, 2013). 

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. 

Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin No. EC225–05A030, Revision 0, 

dated July 12, 2012 (ASB). The ASB 

states that while reconditioning the 

main rotor mast (MRM) assemblies, 

Eurocopter found corrosion on the 

rotating and stationary swashplates 

under the retaining flanges of the 

swashplate sub-assembly bearing. Over 

time, this corrosion could initiate a 

crack. The ASB specifies inspecting the 

MRM assembly for corrosion or a crack 

and replacing the MRM assembly if a 

crack or corrosion is found. The FAA 

and EASA use the term MRH assembly, 

while Eurocopter uses MRM assembly 

to describe the same section of the 

helicopter. 

Costs of Compliance 

We estimate that this AD affects three 

helicopters of U.S. Registry and that 

labor costs average $85 per work-hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting the rotating and 

stationary swashplates for corrosion or a 

crack requires 8 work-hours for a cost of 

$680 per helicopter and $2,040 for the 

U.S. fleet, per inspection cycle. Making 

and installing the placard requires 0.5 

work-hour, for a cost of $43 per 

helicopter. The labor cost of making 

changes to the flight manual is 

negligible. 

• Replacing the MRH assembly 

requires 24 work-hours and parts cost 

$5,000, for a total cost of $7,040 per 

helicopter. 

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 

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): 

2013–26–11 Eurocopter France Helicopters 

(Eurocopter): Amendment 39–17720; 

Docket No. FAA–2013–0635; Directorate 

Identifier 2012–SW–081–AD. 

(a) Applicability 

This AD applies to Eurocopter Model 

EC225LP helicopters with a main rotor hub 

(MRH) assembly with a rotating swashplate, 

part number (P/N) 332A31–3074–00 or 

332A31–3076–00, and stationary swashplate, 

P/N 332A31–3079–00 or 332A31–3079–01, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion or a crack in the stationary or 

rotating swashplate of the MRH assembly, 

which could lead to failure of the swashplate 

and subsequent loss of helicopter control. 


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2368 Federal Register / Vol. 79, No. 9 / Tuesday, January 14, 2014 / Rules and Regulations 

(c) Effective Date 

This AD becomes effective February 18, 

2014. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 110 hours time-in-service (TIS) 

or before the MRH assembly accumulates 

1,320 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,320 

hours TIS, visually inspect the rotating and 

stationary swashplates for corrosion or a 

crack by following the Accomplishment 

Instructions, paragraph 3.B.2 and Figures 1 

through 3, of Eurocopter Alert Service 

Bulletin No. EC225–05A030, Revision 0, 

dated July 12, 2012 (ASB). 

(2) If a crack exists in the rotating or 

stationary swashplates, replace the MRH 

assembly with an airworthy MRH assembly. 

(3) If corrosion exists without any visual 

indication of cracking, do the following: 

(i) Before further flight, install a placard 

stating ‘‘NO FLIGHT IN OAT BELOW ¥30 

°C’’ in the full view of the pilots and add the 

statement ‘‘NO FLIGHT IN OAT BELOW 

¥30 °C’’ to the Operating Limitations Section 

of the helicopter’s Rotorcraft Flight Manual 

(RFM) by making pen and ink changes or by 

inserting a copy of this AD in Section 2.3 

Flight Envelope, Item 2 Temperature Limits. 

(ii) Within 150 hours TIS or 6 months after 

the inspection when the corrosion was first 

detected, whichever occurs first, replace the 

MRH assembly with an airworthy assembly. 

Remove any placard that states ‘‘NO FLIGHT 

IN OAT BELOW ¥30 °C’’ from the helicopter 

and remove any related limitation from the 

RFM. 

(4) Replacement of an MRH assembly does 

not constitute terminating action for the 

repetitive inspections required by paragraph 

(e)(1) of this AD. 

(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 (EASA) 

You may view EASA AD No. 2012–0131, 

dated July 31, 2012 at http://

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0635. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6230, Main Rotor Mast/Swashplate. 

(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 No. 

EC225–05A030, Revision 0, dated July 12, 

2012. 

(ii) Reserved. 

(3) For Eurocopter 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 December 

24, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31447 Filed 1–13–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 95 

[Docket No. 30940; Amdt. No. 511] 

IFR Altitudes; Miscellaneous 

Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts 

miscellaneous amendments to the 

required IFR (instrument flight rules) 

altitudes and changeover points for 

certain Federal airways, jet routes, or 

direct routes for which a minimum or 

maximum en route authorized IFR 

altitude is prescribed. This regulatory 

action is needed because of changes 

occurring in the National Airspace 

System. These changes are designed to 

provide for the safe and efficient use of 

the navigable airspace under instrument 

conditions in the affected areas. 

DATES: Effective 0901 UTC, February 6, 

2014. 

FOR FURTHER INFORMATION CONTACT: 

Harry Hodges, Flight Procedure 

Standards Branch (AMCAFS–420), 

Flight Technologies and Programs 

Division, Flight Standards Service, 

Federal Aviation Administration, Mike 

Monroney Aeronautical Center, 6500 

South MacArthur Blvd. Oklahoma City, 

OK 73169 (Mail Address: P.O. Box 

25082, Oklahoma City, OK 73125) 

telephone: (405) 954–4164. 

SUPPLEMENTARY INFORMATION: This 

amendment to part 95 of the Federal 

Aviation Regulations (14 CFR part 95) 

amends, suspends, or revokes IFR 

altitudes governing the operation of all 

aircraft in flight over a specified route 

or any portion of that route, as well as 

the changeover points (COPs) for 

Federal airways, jet routes, or direct 

routes as prescribed in part 95. 

The Rule 

The specified IFR altitudes, when 

used in conjunction with the prescribed 

changeover points for those routes, 

ensure navigation aid coverage that is 

adequate for safe flight operations and 

free of frequency interference. The 

reasons and circumstances that create 

the need for this amendment involve 

matters of flight safety and operational 

efficiency in the National Airspace 

System, are related to published 

aeronautical charts that are essential to 

the user, and provide for the safe and 

efficient use of the navigable airspace. 

In addition, those various reasons or 

circumstances require making this 

amendment effective before the next 

scheduled charting and publication date 

of the flight information to assure its 

timely availability to the user. The 

effective date of this amendment reflects 

those considerations. In view of the 

close and immediate relationship 

between these regulatory changes and 

safety in air commerce, I find that notice 

and public procedure before adopting 

this amendment are impracticable and 

contrary to the public interest and that 

good cause exists for making the 

amendment effective in less than 30 

days. 

Conclusion 

The FAA has determined that this 

regulation only involves an established 

body of technical regulations for which 

frequent and routine amendments are 

necessary to keep them operationally 

current. It, therefore—(1) is not a 

‘‘significant regulatory action’’ under 


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