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

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

34403 

Vol. 79, No. 116 

Tuesday, June 17, 2014 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0340; Directorate 

Identifier 2014–NM–084–AD; Amendment 

39–17867; AD 2014–12–06] 

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 certain 

Airbus Model A300 B4–600, B4–600R, 

and F4–600R series airplanes, and 

Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes); and Airbus 

Model A310 series airplanes. This AD 

requires inspections of the external area 

of the aft cargo door sill beam for 

cracking, and repair if necessary. This 

AD was prompted by reports of fatigue 

cracks on the cargo door sill beam, lock 

fitting, and torsion box plate. We are 

issuing this AD to detect and correct 

fatigue cracking of the cargo door sill 

beam, lock fitting, and torsion box plate, 

which could result in the loss of the 

door locking function and, 

subsequently, complete loss of the cargo 

door in flight with the risk of rapid 

decompression. 

DATES: This AD becomes effective July 

2, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 2, 2014. 

We must receive comments on this 

AD by August 1, 2014. 

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—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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–2014– 

0340; 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: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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 

Community, has issued EASA 

Emergency Airworthiness Directive 

2014–0097–E, dated April 23, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for certain Airbus Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and Model A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes); and Airbus Model A310 

series airplanes. The MCAI states: 

During accomplishment of Maintenance 

Review Board Report (MRBR) task 531625– 

01–1 on an A300–600 aeroplane having 

accumulated more than 25,000 flight cycles 

(FC) since aeroplane first flight, multiple 

fatigue cracks were found on the following 

parts: 

—Aft cargo door sill beam Part Number 

(P/N) A53973085210 

—Lock fitting P/N A53978239002 

—Torsion box plate P/N A53973318206. 

Prompted by these findings, a stress 

analysis was performed during which it was 

discovered that there is no dedicated 

scheduled maintenance task to inspect the 

affected area for fatigue damage. 

The loss of more than one lock fitting 

could lead to loss of the door locking 

function and, subsequently, complete loss of 

the cargo door in flight with associated risk 

of rapid decompression. 

To address this unsafe condition, Airbus 

issued Alert Operators Transmission (AOT) 

A53W005–14 providing instructions for 

inspection of the affected area. 

For the reason described above, this 

[EASA] AD requires repetitive ultrasonic 

inspections or detailed inspections (DET) for 

cracking of the aft cargo door sill beam 

external area, or a one-time High Frequency 

Eddy Current (HFEC) inspection [for 

cracking] of the aft cargo door sill beam 

internal structure and, depending on 

findings, accomplishment of corrective 

action(s) [e.g. repair]. 

This [EASA] AD is considered an interim 

measure and further AD action may follow. 

You may examine the MCAI on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2014–0340. 

Relevant Service Information 

Airbus has issued Alert Operators 

Transmission A53W005–14, dated April 

22, 2014. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 


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34404 Federal Register / Vol. 79, No. 116 / Tuesday, June 17, 2014 / Rules and Regulations 

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 these same 

type designs. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

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 fatigue cracking of the 

cargo door sill beam, lock fitting, and 

torsion box plate could result in the loss 

of the door locking function and 

subsequently, complete loss of the cargo 

door in flight with the risk of rapid 

decompression. 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–2014–0340; 

Directorate Identifier 2014–NM–084– 

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 170 

airplanes of U.S. registry. 

We also estimate that it will take 

about 11 work-hours 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 $158,950, or $935 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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. 

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): 

2014–12–06 Airbus: Amendment 39–17867. 

Docket No. FAA–2014–0340; Directorate 

Identifier 2014–NM–084–AD. 

(a) Effective Date 

This AD becomes effective July 2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and 

(c)(5) of this AD, certificated in any category, 

all certified models, all manufacturer serial 

numbers on which Airbus Modification 

05438 has been embodied in production, 

except those on which Modification 12046 

has been embodied in production. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes. 

(2) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(3) Airbus Model A300 F4–605R and F4– 

622R airplanes. 


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Federal Register / Vol. 79, No. 116 / Tuesday, June 17, 2014 / Rules and Regulations 34405 

(4) Airbus Model A300 C4–605R Variant F 

airplanes. 

(5) Airbus Model A310–203, –204, –221, 

–222, –304, –322, –324, and –325 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

fatigue cracks on the cargo door sill beam, 

lock fitting, and torsion box plate. We are 

issuing this AD to detect and correct fatigue 

cracking of the cargo door sill beam, lock 

fitting, and torsion box plate, which could 

result in the loss of the door locking function 

and subsequently, complete loss of the cargo 

door in flight with the risk of rapid 

decompression. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Repair 

(1) Within the compliance time identified 

in paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD, as applicable, do an ultrasonic 

inspection or detailed inspection of the aft 

cargo door sill beam external area for 

cracking, in accordance with Airbus Alert 

Operators Transmission (AOT) A53W005–14, 

dated April 22, 2014. Repeat the inspection 

thereafter at intervals not to exceed 275 flight 

cycles. 

(i) For airplanes that have accumulated 

30,000 flight cycles or more since the 

airplane’s first flight as of the effective date 

of this AD: Within 50 flight cycles after the 

effective date of this AD. 

(ii) For airplanes that have accumulated 

18,000 flight cycles or more, but less than 

30,000 flight cycles since the airplane’s first 

flight as of the effective date of this AD: 

Within 275 flight cycles after the effective 

date of this AD. 

(iii) For airplanes that have accumulated 

less than 18,000 flight cycles since the 

airplane’s first flight as of the effective date 

of this AD: Before exceeding 18,275 flight 

cycles since the airplane’s first flight. 

(2) If any crack is found during any 

inspection required by paragraph (g)(1) of 

this AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent, or the Design Approval 

Holder (DAH) with EASA design 

organization approval). 

(h) Optional Terminating Action 

Accomplishment of the high frequency 

eddy current (HFEC) inspection for cracking 

in accordance with Airbus AOT A53W005– 

14, dated April 22, 2014, terminates the 

repetitive inspections required by paragraph 

(g)(1) of this AD for that airplane. If any 

cracking is found during the HFEC 

inspection, before further flight, repair using 

a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA (or 

its delegated agent, or the DAH with EASA 

design organization approval). 

(i) Reporting Requirement 

Submit a report of the findings (both 

positive and negative) of the inspection 

required by paragraph (g)(1) of this AD to 

Airbus as specified in paragraph 7., 

‘‘Reporting’’ of the Airbus AOT A53W005– 

14, dated April 22, 2014, at the applicable 

time specified in paragraph (i)(1) or (i)(2) of 

this AD. The report must include inspection 

results, including no findings. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(j) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or the DAH with a State 

of Design Authority’s design organization 

approval, as applicable). You are required to 

ensure the product is airworthy before it is 

returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Emergency Airworthiness Directive 2014– 

0097–E, dated April 23, 2014, for related 

information. You may examine the MCAI on 

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

searching for and locating Docket No. FAA– 

2014–0340. 

(l) 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 Alert Operators Transmission 

A53W005–14, dated April 22, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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: June 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13832 Filed 6–16–14; 8:45 am] 

BILLING CODE 4910–13–P 


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