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(b) Affected ADs 

This AD replaces AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400F series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 21, Air Conditioning; 31, 

Instruments. 

(e) Unsafe Condition 

This AD was prompted by reports of 

intermittent or blank displays of a certain 

integrated display unit (IDU) in the flight 

deck. We are issuing this AD to prevent IDU 

malfunctions, which could affect the ability 

of the flightcrew to read primary displays for 

airplane attitude, altitude, or airspeed, and 

consequently reduce the ability of the 

flightcrew to maintain control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Software Update 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), with revised service 

information. Within 12 months after January 

16, 2013 (the effective date of AD 2012–24– 

10), except as provided by paragraph (j) of 

this AD: Install integrated display system 

software, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–21A2523, Revision 1, 

dated October 3, 2011; or Boeing Alert 

Service Bulletin 747–21A2523, Revision 2, 

dated June 7, 2013. As of the effective date 

of this AD, only Boeing Alert Service Bulletin 

747–21A2523, Revision 2, dated June 7, 

2013, may be used to accomplish the actions 

required by this paragraph. 

Note 1 to paragraph (g) and (j) of this AD: 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 1, dated October 3, 2011; and 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013; refer to 

Boeing Service Bulletin 747–31–2426, dated 

July 29, 2010 (for airplanes with Rolls-Royce 

engines); Boeing Service Bulletin 747–31– 

2427, dated July 29, 2010 (for airplanes with 

General Electric engines); and Boeing Service 

Bulletin 747–31–2428, dated July 29, 2010 

(for airplanes with Pratt & Whitney engines); 

as additional sources of guidance for the 

software installation specified by paragraph 

(g) of this AD. Boeing Service Bulletin 747– 

31–2426, dated July 29, 2010; Boeing Service 

Bulletin 747–31–2427, dated July 29, 2010; 

and Boeing Service Bulletin 747–31–2428, 

dated July 29, 2010; are not incorporated by 

reference in this AD. 

(h) Retained Duct Assembly Replacement 

and Wiring Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), with revised service 

information. Within 60 months after January 

16, 2013 (the effective date of AD 2012–24– 

10), except as provided by paragraph (j) of 

this AD: Replace the duct assembly with a 

new duct assembly, do wiring changes, and 

route certain wire bundles, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 1, dated October 3, 2011; or Boeing 

Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 747–21A2523, Revision 2, 

dated June 7, 2013, may be used to 

accomplish the actions required by this 

paragraph. 

(i) New Installation of Pressure Switch 

Bracket and Altitude Pressure Switch 

Within 60 months after the effective date 

of this AD: Install a new or serviceable 

pressure switch bracket and a new or 

serviceable altitude pressure switch on the 

forward side of the station 400 bulkhead, do 

wiring changes, route certain wire bundles, 

install a new hose assembly, and perform a 

leak check and a functional logic test, in 

accordance with the Accomplishment 

Instructions of the service information 

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

AD, as applicable. 

(1) For Model 747–400F series airplanes: 

Boeing Alert Service Bulletin 747–21–2532, 

dated February 13, 2014. 

(2) For Model 747–400BCF series 

airplanes: Boeing Alert Service Bulletin 747– 

21–2533, dated February 13, 2014. 

(j) Actions for Group 21 Airplanes 

For Group 21 airplanes, as identified in 

Boeing Alert Service Bulletin 747–21A2523, 

Revision 2, dated June 7, 2013, do the actions 

specified in paragraphs (j)(1) and (j)(2) of this 

AD, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–21A2523, Revision 2, dated June 7, 

2013. 

(1) Within 12 months after the effective 

date of this AD, install integrated display 

system software. 

(2) Within 60 months after the effective 

date of this AD, replace the duct assembly 

with a new duct assembly, do wiring 

changes, and route certain wire bundles. 

(k) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–21A2523, Revision 1, 

dated October 3, 2011. 

(l) 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 (m)(1) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2012–24–10, 

Amendment 39–17280 (77 FR 73908, 

December 12, 2012), are approved as AMOCs 

for the corresponding provisions of 

paragraphs (g) and (h) of this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Ana Martinez Hueto, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6592; fax: 425–917–6591; 

email: ana.m.hueto@faa.gov. 

(2) 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://www.myboeingfleet.com. You 

may view this referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

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

Issued in Renton, Washington, on February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02925 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0243; Directorate 

Identifier 2014–NM–114–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 

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Airbus Model A300 series airplanes; 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and A300 C4– 

605R Variant F airplanes (collectively 

called Model A300–600 series 

airplanes); and Model A310 series 

airplanes. This proposed AD was 

prompted by reports of cracked 

aluminum support struts of the 

trimmable horizontal stabilizer (THS) 

caused by stress corrosion. This 

proposed AD would require inspections 

to identify the part number of each 

support strut, repetitive inspections for 

cracking of the THS support strut ends, 

installation of reinforcing clamps on 

strut ends, and replacement of support 

struts, if necessary. We are proposing 

this AD to detect and correct cracked 

THS support struts, which could lead to 

the rupture of all four support struts 

making the remaining structure unable 

to carry limit loads, which could result 

in loss of the THS and reduced control 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 6, 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 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–2015– 

0243; 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, WA 

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 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0243; Directorate Identifier 

2014–NM–114–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 

Union, has issued EASA Airworthiness 

Directive 2014–0164, dated July 11, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A300 series airplanes; Model 

A300 B4–600, B4–600R, and F4–600R 

series airplanes, and A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes); and 

Model A310 series airplanes. The MCAI 

states: 

During scheduled maintenance, several 

Trimmable Horizontal Stabilizer (THS) 

support struts were found cracked at the strut 

ends. The THS is supported and articulated 

at frame (FR) 91 in the tail cone. Lateral 

movement is prevented by four diagonal 

support struts. 

Investigations revealed that the cracks were 

caused by stress corrosion and propagated 

from the inside to the outside of the strut. 

This condition, if not detected and 

corrected, could lead to the rupture of all 

four THS support struts at FR91, which 

would make the remaining structure unable 

to carry limit loads, potentially resulting in 

loss of the Horizontal Tail Plane. 

To address this unsafe condition, EASA 

issued [EASA] AD 2014–0121 [http://

ad.easa.europa.eu/ad/2014-0121] to require 

repetitive High Frequency Eddy Current 

(HFEC) inspections of the THS support strut 

ends, installation of reinforcing clamps on 

strut ends and, depending on findings, 

replacement of damaged support struts. 

Installation of reinforcing clamps on strut 

ends is considered a temporary solution 

pending introduction of a re-designed 

support strut. 

Since that [EASA] AD was issued, it was 

discovered that the [EASA] AD appeared to 

also require HFEC inspections of steel struts, 

which are not prone to cracking. The unsafe 

condition exists only on support struts made 

of aluminum, which were introduced 

through Airbus modification (mod) 06101, 

but may also have been installed in service 

as replacement parts on aeroplanes in premod 06101 configuration. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0121, which is superseded, and 

clarifies the need for an initial identification 

of the support struts installed on aeroplanes 

in pre-mod 06101 configuration. The related 

Airbus Service Bulletins (SB) remain 

unchanged. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0243. 

Relevant Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

• Airbus Service Bulletin A300–53– 

0394, dated February 14, 2014. This 

service information describes 

procedures for reinforcing the support 

struts of the THS at frame 91 in the 

fuselage tail section of Airbus Model 

A300 series airplanes. 

• Airbus Service Bulletin A300–53– 

0395, dated February 14, 2014. This 

service information describes 

procedures for inspecting for cracking of 

the support struts of the THS at frame 

91 in the fuselage tail section of Airbus 

Model A300 series airplanes. 

• Airbus Service Bulletin A300–53– 

6172, dated February 14, 2014. This 

service information describes 

procedures for reinforcing the support 

struts of the THS at frame 91 in the 

fuselage tail section of Airbus Model 

A300–600 series airplanes. 

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• Airbus Service Bulletin A300–53– 

6174, dated February 14, 2014. This 

service information describes 

procedures for inspecting for cracking of 

the support struts of the THS at frame 

91 in the fuselage tail section of Airbus 

Model A300–600 series airplanes. 

• Airbus Service Bulletin A310–53– 

2136, dated February 14, 2014. This 

service information describes 

procedures for reinforcing the support 

struts of the THS at frame 91 in the 

fuselage tail section of Airbus Model 

A310 series airplanes. 

• Airbus Service Bulletin A310–53– 

2137, dated February 14, 2014. This 

service information describes 

procedures for inspecting for cracking of 

the support struts of the THS at frame 

91 in the fuselage tail section of Airbus 

Model A310 series airplanes. This 

service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

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 these same 

type designs. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

Unlike the procedures described in 

Airbus Service Bulletin A300–53–0395; 

Airbus Service Bulletin A300–53–6174; 

and Airbus Service Bulletin A310–53– 

2137; each dated February 14, 2014; this 

proposed AD would not permit further 

flight if cracks are detected in the 

aluminum support strut ends of the 

trimmable horizontal stabilizer at frame 

91. We have determined that, because of 

the safety implications and 

consequences associated with that 

cracking, any cracked aluminum 

support strut ends of the trimmable 

horizontal stabilizer must be repaired or 

modified before further flight. This 

difference has been coordinated with 

EASA and Airbus. 

Costs of Compliance 

We estimate that this proposed AD 

affects 174 airplanes of U.S. registry. 

We also estimate that it would take 

about 5 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 about $2,100 per 

product. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $439,350, or $2,525 

per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 15 work-hours and require parts 

costing $10,000, for a cost of $11,275 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

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 proposed AD is 2120– 

0056. The paperwork cost associated 

with this proposed 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 proposed 

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 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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2015–0243; 

Directorate Identifier 2014–NM–114–AD. 

(a) Comments Due Date 

We must receive comments by April 6, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1) through (c)(6) 

of this AD, certificated in any category, all 

manufacturer serial numbers. 

(1) Airbus Model A300 B2–1A, B2–1C, 

B2K–3C, B2–203, B4–2C, B4–103, and B4– 

203 airplanes. 

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

B4–620, and B4–622 airplanes. 

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

622R airplanes. 

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

622R airplanes. 

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

airplanes. 

(6) 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 

cracked aluminum support struts of the 

trimmable horizontal stabilizer (THS) caused 

by stress corrosion. We are issuing this AD 

to detect and correct cracked THS support 

struts, which could lead to the rupture of all 

four support struts making the remaining 

structure unable to carry limit loads, which 

could result in loss of the THS and reduced 

control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection for Part Number 

For airplanes in pre-modification 06101 

configuration: Within 12 months after the 

effective date of this AD, do an inspection to 

identify the part number (P/N) of each 

support strut installed on the trimmable 

horizontal stabilizer (THS) at frame (FR) 91, 

in accordance with the Accomplishment 

Instructions of the applicable service bulletin 

identified in paragraphs (g)(1) through (g)(3) 

of this AD. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection, provided those records can be 

relied upon for that purpose and the part 

number can be positively identified from that 

review. If no aluminum strut(s) having P/N 

R21449, R21449D, R21449G, or R21449H is 

found during any inspection required by this 

paragraph no further action is required by 

this AD for that horizontal stabilizer, except 

for paragraph (l) of this AD. 

(1) For Airbus Model A300 series 

airplanes: Airbus Service Bulletin A300–53– 

0395, dated February 14, 2014. 

(2) For Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 series 

airplanes): Airbus Service Bulletin A300–53– 

6174, dated February 14, 2014. 

(3) For Airbus Model A310 series 

airplanes: Airbus Service Bulletin A310–53– 

2137, dated February 14, 2014. 

(h) Repetitive High Frequency Eddy Current 

(HFEC) Inspections 

For airplanes in post-modification 06101 

configuration; and for airplanes in premodification 06101 configuration on which 

one or more aluminum support strut(s) 

having P/N R21449, P/N R21449D, P/N 

R21449G, or P/N R21449H was found during 

the inspection by paragraph (g) of this AD: 

Within the applicable compliance times 

specified in paragraphs (h)(1), (h)(2), or (h)(3) 

of this AD, do an HFEC inspection for 

cracking of the aluminum THS support strut 

ends at FR 91, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (g)(1) through (g)(3) of this AD. 

Reinforcing clamps already installed on strut 

ends must be removed before accomplishing 

the HFEC inspection and re-installed after 

the inspection, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin specified in 

paragraphs (g)(1) through (g)(3) of this AD. 

Repeat the inspection thereafter at intervals 

not to exceed 24 months. 

(1) For airplanes having manufacturer 

serial number (MSN) 0499 through MSN 

0747 inclusive (post-mod 06101): Within 12 

months after the effective date of this AD. 

(2) For airplanes having MSN 0748 through 

MSN 0878 inclusive (post-mod 06101): 

Within 18 months after the effective date of 

this AD. 

(3) For airplanes having MSN 0001 through 

MSN 0498 inclusive (pre-mod 06101) having 

one or more aluminum struts: Within 24 

months after the effective date of this AD. 

(i) Installation of Reinforcing Clamps 

Concurrently with the initial HFEC 

inspection required by paragraph (h) of this 

AD, identify struts having P/N R21449, P/N 

R21449D, P/N R21449G, or P/N R21449H 

with no reinforcing clamps previously 

installed, and before next flight, install 

reinforcing clamps on each strut end, in 

accordance with the Accomplishment 

Instructions of the applicable service bulletin 

specified in paragraphs (i)(1) through (i)(3) of 

this AD. 

(1) For Airbus Model A300 series 

airplanes: Airbus Service Bulletin A300–53– 

0394, dated February 14, 2014. 

(2) For Airbus Model A300 B4–600, B4– 

600R, and F4–600R series airplanes, and 

A300 C4–605R Variant F airplanes 

(collectively called Model A300–600 series 

airplanes): Airbus Service Bulletin A300–53– 

6172, dated February 14, 2014. 

(3) For Airbus Model A310 series 

airplanes: Airbus Service Bulletin A310–53– 

2136, dated February 14, 2014. 

(j) Corrective Actions 

If, during any inspection required by 

paragraph (h) of this AD, any cracking is 

found, before further flight, replace the 

affected THS support strut(s) with 

serviceable struts and install clamps on each 

strut end, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraphs (g)(1) through (g)(3) of this AD. 

(k) Clarification 

Installation of reinforcing clamps as 

required by paragraph (i) of this AD, and the 

replacement of support struts and/or the 

installation of clamps as required by 

paragraph (j) of this AD, do not constitute 

terminating action for the repetitive 

inspections required by paragraph (h) of this 

AD. 

(l) Reporting 

At the applicable time specified in 

paragraphs (l)(1) and (l)(2) of this AD: After 

accomplishment of any inspection required 

by paragraphs (g) and (h) of this AD, report 

all inspection results to Airbus, including no 

findings, in accordance with the 

Accomplishment Instructions of the 

applicable service bulletins specified in 

paragraphs (g)(1) through (g)(3) of this AD, 

and paragraphs (i)(1) through (i)(3) of this 

AD. 

(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. 

(m) 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) 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. 

(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. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 80, No. 32 / Wednesday, February 18, 2015 / Proposed Rules 8575 

Aviation Safety Agency Airworthiness 

Directive 2014–0164, dated July 11, 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–2015–0243. 

(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 February 

2, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02922 Filed 2–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0086; Directorate 

Identifier 2014–NM–191–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 A310–203 airplanes. This 

proposed AD is intended to complete 

certain mandated programs intended to 

support the airplane reaching its limit of 

validity (LOV) of the engineering data 

that support the established structural 

maintenance program. This proposed 

AD was prompted by reports that side 

link clevis bolts of the front engine 

mount do not meet the Design Service 

Goal (DSG) requirements on airplanes 

equipped with General Electric 

Company CF6–80A3 engines. This 

proposed AD would require repetitive 

replacement of all side link clevis 

engine mount bolts. We are proposing 

this AD to prevent failure of the front 

engine mount, and consequent possible 

departure of the engine. 

DATES: We must receive comments on 

this proposed AD by April 6, 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 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–2015– 

0086; 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 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–0086; Directorate Identifier 

2014–NM–191–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 

As described in FAA Advisory 

Circular 120 104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120-104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a LOV of the engineering data 

that support the structural maintenance 

program under 14 CFR 26.21. This 

proposed AD is the result of an 

assessment of the previously established 

programs by Airbus during the process 

of establishing the LOV for Airbus 

Model A310–203 airplanes. The actions 

specified in this proposed AD are 

necessary to complete certain programs 

to ensure the continued airworthiness of 

aging airplane structure and to support 

an airplane reaching its LOV. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0191, dated August 29, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all Airbus 

Model A310–203 airplanes. The MCAI 

states: 

During fatigue analysis performed in the 

scope of the Extended Service Goal, taking 

into account the certification loads and the 

new lift-off loads, Airbus determined that 

side link clevis engine mount bolts do not 

meet the Design Service Goal (DSG) 

requirements on aeroplanes equipped with 

CF6–80A3 engines. 

This condition, if not corrected, could lead 

to failure of the front engine mount, possibly 

resulting in-flight separation of the engine 

from the aeroplane. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A310– 

71–2038 to introduce a life limit on the side 

link clevis engine mount bolts. 

For the reason described above, this 

[EASA] AD requires implementation of the 

new life limit and replacement of all side 

link clevis engine mount bolts that have 

exceeded the new limit. 

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