Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20837 

FIGURE 1 TO PARAGRAPH (G) OF THIS AD: ENGINE SHUT-OFF VALVE (FUEL SPAR VALVE) POSITION INDICATION

OPERATIONAL CHECK—Continued 

AWL Number Task Interval Applicability Description 

NOTE: It is normal under this test condition for the ENG 

VALVE CLOSED indication light on the OVERHEAD 

PANEL to transition from DIM to BRIGHT and stay 

BRIGHT. 

b. Move ENG 2 START LEVER on the CONTROL STAND 

to the CUTOFF position. 

c. Verify the SPAR VALVE CLOSED indication light on the 

OVERHEAD PANEL for No. 2 Engine changes from 

OFF to BRIGHT then DIM. 

d. If the test fails, (bright light fails to illuminate), before further flight, repair faults as required (refer to Boeing AMM 

28–22–11). 

(h) No Alternative Actions and Intervals 

After accomplishment of the maintenance 

or inspection program revision required by 

paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO) 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(j) Related Information 

For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6509; fax: (425) 917–6590; 

email: rebel.nichols@faa.gov. 

Issued in Renton, Washington, on April 4, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–08320 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0230; Directorate 

Identifier 2013–NM–242–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A300–600 series 

airplanes. This proposed AD was 

prompted by reports of cracking found 

in the pylon box, which was due to the 

stresses resulting from the pressure 

applied by the engines’ thrust reverser 

cowl bumpers. This proposed AD would 

require repetitive high frequency eddy 

current (HFEC) inspections for cracking, 

and replacement of all fittings if 

necessary. Replacement of all fittings 

would terminate the repetitive HFEC 

inspections. We are proposing this AD 

to detect and correct cracks of the pylon 

rib 5, which could result in reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 29, 2014. 

ADDRESSES: You may send comments 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 proposed 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– 

0230; 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 proposed 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, 

Washington 98057–3356; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

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20838 Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0230; Directorate Identifier 

2013–NM–242–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0286, 

dated December 4, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Cracks were found on the lower side of rib 

5 in the pylon box on A300 aeroplanes 

powered with General Electric engines. 

Investigations revealed that these cracks 

were due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

Airbus developed an inspection 

programme to detect the cracks and 

associated actions to correct them. 

For the reasons described above, this 

[EASA] AD requires repetitive [HFEC] 

inspections of the pylon rib 5 on the left 

hand side (LH) and right hand (RH) side and, 

when cracks are detected, replacement of the 

affected structural part(s) [Replacement of all 

fittings would terminate the repetitive HFEC 

inspections.] 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2014–0230. 

Relevant Service Information 

Airbus has issued the following 

service bulletins. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

• Airbus Service Bulletin A300–54– 

6031, dated May 30, 1996. 

• Airbus Mandatory Service Bulletin 

A300–54–6034, Revision 02, dated 

August 26, 2013. 

FAA’s Determination and Requirements 

of This Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

While paragraph (2) of EASA AD 

2013–0286, dated December 4, 2013, 

gives a compliance time of within 250 

flight hours to replace fittings, this AD 

requires replacement of those fitting 

before further flight. 

Costs of Compliance 

We estimate that this proposed AD 

affects 129 airplanes of U.S. registry. 

We also estimate that it would take 

about 9 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost $0 per product. Based 

on these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $98,685 or $765 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 32 work-hours and require parts 

costing $2,450, for a cost of $5,170 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Airbus: Docket No. FAA–2014–0230; 

Directorate Identifier 2013–NM–242–AD. 

(a) Comments Due Date 

We must receive comments by May 29, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, B4–622, B4–605R, B4– 

622R, F4–605R, F4–622R, and C4–605R 

Variant F airplanes, certificated in any 

category, all manufacturer serial numbers, 

except those on which Airbus Modification 

11110 has been embodied in production, or 

that have been modified in service as 

specified in Airbus Service Bulletin A300– 

54–6031, dated May 30, 1996. 

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Federal Register / Vol. 79, No. 71 / Monday, April 14, 2014 / Proposed Rules 20839 

(d) Subject 

Air Transport Association (ATA) of 

America Code 54, Nacelles/Pylons. 

(e) Reason 

This AD was prompted by reports of 

cracking found in the pylon box, which was 

due to the stresses resulting from the 

pressure applied by the thrust reverser cowl 

bumpers. We are issuing this AD to detect 

and correct cracks of the pylon rib 5, which 

could result in reduced structural integrity of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Replacement 

(1) Before the accumulation of 15,000 total 

flight hours since the airplane’s first flight, or 

within 6,000 flight hours after the effective 

date of this AD, whichever occurs later, do 

a high frequency eddy current (HFEC) 

inspection for cracking on the lower area of 

rib 5 on the left-hand and right-hand side 

pylons, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A300–54–6034, 

Revision 02, dated August 26, 2013. Repeat 

the inspection thereafter at intervals not to 

exceed 15,000 flight hours. 

(2) If any crack is found during any 

inspection required by paragraph (g)(1) of 

this AD, before further flight, replace all the 

fittings with new standard fittings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

54–6031, dated May 30, 1996. 

(h) Terminating Action 

Replacement of all fittings as required by 

paragraph (g)(2) of this AD, or modification 

of pylons in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–54–6031, dated May 

30, 1996, terminates the repetitive HFEC 

inspections required by paragraph (g)(1) of 

this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

inspections required by paragraph (g)(1) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A300–54–6034, 

Revision 01, dated September 14, 1999, 

which is not incorporated by reference in 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, Washington 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). You are required to ensure the 

product is airworthy before it is returned to 

service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0286, dated December 4, 

2013, 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 it in Docket No. 

FAA–2014–0230. 

(2) 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 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. 

Issued in Renton, Washington, on April 1, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–08303 Filed 4–11–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0228 Directorate 

Identifier 2013–NM–216–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–200 Freighter, 

A330–200 and –300, and A340–200, 

–300, –500, and –600 series airplanes. 

This proposed AD was prompted by 

reassessment of an unsafe condition 

related to MZ-type spoiler servocontrols (SSCs) that did not remain 

locked in the retracted position 

(hydraulic locking function) after 

manual depressurization of the 

corresponding hydraulic circuit. This 

reassessment resulted in the 

determination that performing repetitive 

operational tests of all SSC types is 

necessary. This proposed AD would 

require repetitive operational tests of the 

hydraulic locking function on each SSC 

installed on the blue or yellow 

hydraulic circuits, and replacing any 

affected SSC with a serviceable SSC. We 

are proposing this AD to detect and 

correct loss of the hydraulic locking 

function during take-off, which, in 

combination with one inoperative 

engine, could result in reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by May 29, 2014. 

ADDRESSES: You may send comments 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 proposed 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; 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 

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