4762 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 

In the rule, the FAA amended certain 

airworthiness regulations for transport 

category airplanes to eliminate 

regulatory differences between the 

airworthiness standards of the FAA and 

European Aviation Safety Agency 

(EASA). It does not add new 

requirements beyond what 

manufacturers currently meet for EASA 

certification and does not affect current 

industry design practices. This final rule 

revises the pitch maneuver design loads 

criteria; revises the gust and turbulence 

design loads criteria; revises the 

application of gust loads to engine 

mounts, high lift devices, and other 

control surfaces; adds a ‘‘round-theclock’’ discrete gust criterion and a 

multi-axis discrete gust criterion for 

airplanes equipped with wing-mounted 

engines; revises the engine torque loads 

criteria; adds an engine failure dynamic 

load condition; revises the ground gust 

design loads criteria; revises the criteria 

used to establish the rough air design 

speed; and requires the establishment of 

a rough air Mach number. 

This document corrects three errors in 

the Greek letters and subscripts 

contained in various equations in the 

regulatory text. In one case, the ‘‘U’’ in 

the equation is changed from subscript 

to regular, uppercase text. In another 

case, instead of ‘‘PL = PL–1g ± UsA ̄ ’’, the 

equation should be ‘‘PL = PL–1g ± UsA ̄ ’’. 

In two cases, the three Greek letters 

‘‘rej’’ after sigma ‘‘s’’ in the subscript 

of ‘‘U’’ are changed to ‘‘ref’’. In these 

cases, ‘‘Usrej’’ should be ‘‘Usref’’. 

This correction also corrects the 

statement in the rule’s preamble that the 

FAA received 33 comments to the 

Advisory Circulars, rather than none. 

Corrections 

In FR Doc. 2014–28938, beginning on 

page 73464, in the Federal Register of 

December 11, 2014, make the following 

corrections: 

1. On Page 73464, second column, 

under the heading ‘‘C. Advisory 

Material’’, the sentence, ‘‘The FAA did 

not receive any comments on the 

proposed ACs’’ is corrected to read ‘‘The 

FAA received 33 comments on the 

proposed ACs. These comments did not 

have an impact on the regulatory 

requirements’’. 

2. On page 73467, second column, 

line 11, the equation ‘‘PL = PL–1g ± UsA ̄ ’’ 

is corrected to read ‘‘PL = PL–1g ± UsA ̄ ’’. 

3. On page 73467, second column, 

fifth line from the bottom, the equation 

‘‘Us = UsrejFg’’ is corrected to read 

‘‘Us = Usref Fg’’. 

4. On page 73467, second column, 

third line from the bottom, the text 

‘‘Usrej’’ is corrected to read ‘‘Usref’’. 

Issued in Washington, DC, on January 16, 

2015. 

Lirio Liu, 

Director, Office of Rulemaking. 

[FR Doc. 2015–01205 Filed 1–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0078; Directorate 

Identifier 2014–NM–235–AD; Amendment 

39–18084; AD 2015–02–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A330–200, A330–200 

Freighter, and A330–300 series 

airplanes. This AD requires revising the 

electrical emergency configuration 

procedure in the Emergency Procedures 

section of the airplane flight manual 

(AFM) to include procedures for 

deploying the ram air turbine manually 

to provide sufficient hydraulic power 

and avoid constant speed motor/

generator (CSM/G) shedding. This AD 

was prompted by an electrical load 

analysis that revealed that hydraulic 

power might not be sufficient to supply 

the CSM/G during slat/flap extension 

when only one engine is running. We 

are issuing this AD to prevent such a 

condition which, in conjunction with 

the loss of the main electrical system, 

could lead to the scenario where the 

flightcrew is not clearly warned that the 

electrical system has switched on the 

battery and thus has a limited duration 

that would allow a safe landing. 

DATES: This AD becomes effective 

February 13, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 13, 2015. 

We must receive comments on this 

AD by March 16, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For 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. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0078; 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0281, dated December 

22, 2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition on all Airbus Model 

A330–200, A330–200 Freighter, and 

A330–300 series airplanes. The MCAI 

states: 

The Constant Speed Motor/Generator 

(CSM/G), as installed on Airbus A330 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 4763 

aeroplanes, is qualified for an overload 

condition of 9.5kVA [kilovolt-ampere] for 30 

minutes. This duration is sufficient to 

perform safe landing and a GO–AROUND. 

However, electrical load analysis revealed 

that the hydraulic power might not be 

sufficient to supply the CSM/G during slat/ 

flap extension when only one engine is 

running. 

This condition, if not corrected, and in 

conjunction with the loss of main electrical 

system, could lead to the scenario where the 

crew is not clearly warned that the electrical 

system has switched on the battery and thus 

has a limited duration that would allow a 

safe landing. 

To address this potential unsafe condition, 

Airbus issued an Aircraft Flight Manual 

(AFM) Temporary Revision (TR) on A330 

aeroplane to update the electrical emergency 

configuration ‘‘ELEC EMER CONFIG’’ 

procedure to require the pilot to deploy the 

ram air turbine manually before setting the 

Landing Recovery to ON position to provide 

sufficient hydraulic power and avoid CSM/ 

G shedding under worst-case operational 

conditions. 

Consequently, EASA issued AD 2014–0273 

(http://ad.easa.europa.eu/blob/easa_ad_

2014_0273_superseded.pdf/AD_2014-0273_

1) to require amendment of the AFM by 

incorporating the applicable Airbus TR. 

After that [EASA] AD was issued, EASA 

became aware that the reference to Airbus 

modification (mod) 47930 was insufficient to 

define which AFM TR is applicable to which 

aeroplane (configuration), as this mod can be 

embodied in service with Airbus Service 

Bulletin (SB) A330–28–3067. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0273, which is superseded, and 

corrects the information included in Table 1. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0078. 

Related Service Information 

Airbus has issued A330/A340 

Airplane Flight Manual (AFM) 

Temporary Revision (TR) TR427, 

UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated 

November 7, 2014 (for airplanes in 

Airbus pre-modification 47930 

configuration or pre-Airbus Service 

Bulletin A330–28–3067 configuration); 

and A330/A340 AFM TR TR428, 

UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated 

November 7, 2014 (for airplanes in 

Airbus post-modification 47930 

configuration or post-Airbus Service 

Bulletin A330–28–3067 configuration). 

This service information describes 

updated electrical emergency 

configuration procedures in the AFM. 

You can find this information at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2015– 

0078. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because hydraulic power might not 

be sufficient to supply the CSM/G 

during slat/flap extension when only 

one engine is running. This condition, 

in conjunction with the loss of the main 

electrical system, could lead to the 

scenario where the flightcrew is not 

clearly warned that the electrical system 

has switched on the battery and thus 

has a limited duration that would allow 

a safe landing. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2015–0078; 

Directorate Identifier 2014–NM–235– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD based on those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 91 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour 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 on U.S. 

operators to be $7,735, or $85 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 that 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); 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


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4764 Federal Register / Vol. 80, No. 19 / Thursday, January 29, 2015 / Rules and Regulations 

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): 

2015–02–17 Airbus: Amendment 39–18084. 

Docket No. FAA–2015–0078; Directorate 

Identifier 2014–NM–235–AD. 

(a) Effective Date 

This AD becomes effective February 13, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243, and –243F airplanes. 

(2) Airbus Model A330–301, –302, –303, 

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

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 24, Electrical Power. 

(e) Reason 

This AD was prompted by an electrical 

load analysis that revealed that hydraulic 

power might not be sufficient to supply the 

constant speed motor/generator (CSM/G) 

during slat/flap extension when only one 

engine is running. We are issuing this AD to 

prevent such a condition which, in 

conjunction with the loss of the main 

electrical system, could lead to the scenario 

where the flightcrew is not clearly warned 

that the electrical system has switched on the 

battery and thus has a limited duration that 

would allow a safe landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revise Airplane Flight Manual (AFM) 

Within 15 days after the effective date of 

this AD, revise the Emergency Procedures 

section of the Airbus A330 AFM to include 

the information in the applicable Airbus 

temporary revision (TR) specified in 

paragraph (g)(1) or (g)(2) of this AD. This may 

be done by inserting a copy of the applicable 

TR specified in paragraph (g)(1) or (g)(2) of 

this AD into the AFM. Operate the airplane 

according to the procedures in the applicable 

TR. When the information in the applicable 

TR has been included in the general revisions 

of the AFM, the general revisions may be 

inserted into the AFM, provided the relevant 

information in the general revision is 

identical to that in the TR, and the TR may 

be removed. 

(1) For airplanes in Airbus premodification 47930 configuration and preAirbus Service Bulletin A330–28–3067 

configuration: Airbus A330/A340 AFM TR 

TR427, UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 

(2) For airplanes in Airbus postmodification 47930 configuration or postAirbus Service Bulletin A330–28–3067 

configuration: Airbus A330/A340 AFM TR 

TR428, UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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, WA 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0281, dated 

December 22, 2014, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–0078. 

(j) 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 this AD specifies otherwise. 

(i) Airbus A330/A340 Airplane Flight 

Manual (AFM) Temporary Revision TR427, 

UPDATE OF ELEC—EMER CONFIG 

PROCEDURE, Issue 1.0, dated November 7, 

2014. 

(ii) Airbus A330/A340 AFM Temporary 

Revision TR428, UPDATE OF ELEC—EMER 

CONFIG PROCEDURE, Issue 1.0, dated 

November 7, 2014. 

(3) For 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. 

(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(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 Renton, Washington, on January 

9, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–01178 Filed 1–28–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0683; Directorate 

Identifier 2010–NE–25–AD; Amendment 39– 

18065; AD 2015–02–01] 

RIN 2120–AA64 

Airworthiness Directives; Technify 

Motors GmbH (Type Certificate 

Previously Held by Thielert Aircraft 

Engines GmbH) Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2011–23– 

01 for all Technify Motors GmbH (TMG) 

models TAE 125–01 and TAE 125–02– 

99 reciprocating engines with certain 

part number (P/N) and serial number (S/ 

N) clutch assemblies installed. AD 

2011–23–01 required replacement of 

certain P/N and S/N clutch assemblies. 

This AD requires the same actions but 


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