11960 Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 

Conclusion 

This action affects only certain novel 

or unusual design features on two 

model series of airplanes. It is not a rule 

of general applicability. 

List of Subjects in 14 CFR Part 25 

Aircraft, Aviation safety, Reporting 

and recordkeeping requirements. 

The authority citation for these 

special conditions is as follows: 

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

44702, 44704. 

The Proposed Special Conditions 

■ Accordingly, the Federal Aviation 

Administration proposes the following 

special conditions as part of the type 

certification basis for Bombardier 

Aerospace BD–500–1A10 and BD–500– 

1A11 series airplanes. 

1. Electronic Flight Control System: 

Lateral-Directional and Longitudinal 

Stability and Low-Energy Awareness. In 

lieu of the requirements of §§ 25.171, 

25.173, 25.175, and 25.177: 

(a) The airplane must be shown to 

have suitable static lateral, directional, 

and longitudinal stability in any 

condition normally encountered in 

service, including the effects of 

atmospheric disturbance. The showing 

of suitable static lateral, directional, and 

longitudinal stability must be based on 

the airplane handling qualities, 

including pilot workload and pilot 

compensation, for specific test 

procedures during the flight test 

evaluations. 

(b) The airplane must provide 

adequate awareness to the pilot of a low 

energy (low speed/low thrust/low 

height) state when fitted with flight 

control laws presenting neutral 

longitudinal stability significantly 

below the normal operating speeds. 

‘‘Adequate awareness’’ means warning 

information must be provided to alert 

the crew of unsafe operating conditions 

and to enable them to take appropriate 

corrective action. 

(c) The static directional stability (as 

shown by the tendency to recover from 

a skid with the rudder free) must be 

positive for any landing gear and flap 

position and symmetrical power 

condition, at speeds from 1.13 VSR1, up 

to VFE, VLE, or VFC/MFC (as appropriate). 

(d) The static lateral stability (as 

shown by the tendency to raise the low 

wing in a sideslip with the aileron 

controls free), for any landing-gear and 

wing-flap position and symmetricpower condition, may not be negative at 

any airspeed (except that speeds higher 

than VFE need not be considered for 

wing-flaps-extended configurations nor 

speeds higher than VLE for landing-gearextended configurations) in the 

following airspeed ranges: 

i. From 1.13 VSR1 to VMO/MMO. 

ii. From VMO/MMO to VFC/MFC, unless 

the divergence is— 

(1) Gradual; 

(2) Easily recognizable by the pilot; 

and 

(3) Easily controllable by the pilot. 

(e) In straight, steady sideslips over 

the range of sideslip angles appropriate 

to the operation of the airplane, but not 

less than those obtained with one half 

of the available rudder control 

movement (but not exceeding a rudder 

control force of 180 pounds), rudder 

control movements and forces must be 

substantially proportional to the angle 

of sideslip in a stable sense; and the 

factor of proportionality must lie 

between limits found necessary for safe 

operation. This requirement must be 

met for the configurations and speeds 

specified in paragraph (c) of this 

section. 

(f) For sideslip angles greater than 

those prescribed by paragraph (e) of this 

section, up to the angle at which full 

rudder control is used or a rudder 

control force of 180 pounds is obtained, 

the rudder control forces may not 

reverse, and increased rudder deflection 

must be needed for increased angles of 

sideslip. Compliance with this 

requirement must be shown using 

straight, steady sideslips, unless full 

lateral control input is achieved before 

reaching either full rudder control input 

or a rudder control force of 180 pounds; 

a straight, steady sideslip need not be 

maintained after achieving full lateral 

control input. This requirement must be 

met at all approved landing gear and 

wing-flap positions for the range of 

operating speeds and power conditions 

appropriate to each landing gear and 

wing-flap position with all engines 

operating. 

Issued in Renton, Washington, on February 

24, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–05048 Filed 3–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0251; Directorate 

Identifier 2014–NM–200–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 A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a determination 

that, in specific flight conditions, the 

allowable load limits on the vertical tail 

plane could be reached and possibly 

exceeded. Exceeding allowable load 

could result in detachment of the 

vertical tail plane. This proposed AD 

would require modification of the pin 

programming flight warning computer 

(FWC) to activate the stop rudder input 

warning (SRIW) logic; and an inspection 

to determine the part numbers of the 

FWC and the flight augmentation 

computer (FAC), and replacement of the 

FWC and FAC if necessary. We are 

proposing this AD to prevent 

detachment of the vertical tail plane and 

consequent loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by April 20, 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, 

Airworthiness Office—EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

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

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Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 11961 

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– 

0251; 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

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–2015–0251; Directorate Identifier 

2014–NM–200–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 2014–0217, 

dated September 26, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Model A318, A319, A320, and 

Model A321 series airplanes. The MCAI 

states: 

During design reviews that were conducted 

following safety recommendations related to 

in-service incidents and one accident on 

another aircraft type, it has been determined 

that, in specific flight conditions, the 

allowable load limits on the vertical tail 

plane could be reached and possibly 

exceeded. 

This condition, if not corrected, could lead, 

in the worst case, to detachment of the 

vertical tail plane in flight and consequent 

loss of the aeroplane. 

To prevent such a possibility, Airbus has 

developed modifications within the flight 

augmentation computer (FAC) to reduce the 

vertical tail plane stress and to activate a 

conditional aural warning within the flight 

warning computer (FWC) to further protect 

against pilot induced rudder doublets. 

For the reasons described above, this 

[EASA] AD requires installation and 

activation of the stop rudder input warning 

(SRIW) logic. 

In addition, this [EASA] AD requires, prior 

to or concurrent with modification of an 

aeroplane with the activation of the SRIW, 

upgrades of the FAC and FWC, to introduce 

the SRIW logic and SRIW aural capability, 

respectively. After modification, this [EASA] 

AD prohibits installation of certain Part 

Number (P/N) FWC and FAC. 

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– 

0251. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–22–1480, dated July 9, 2014. The 

service information describes 

procedures for modifying the pin 

programming to activate the SRIW logic. 

Airbus has also issued the following 

service bulletins. The service 

information describes procedures for 

replacing FWCs and FACs. 

• Airbus Service Bulletin A320–22– 

1375, dated January 15, 2014. 

• Airbus Service Bulletin A320–22– 

1427, Revision 04, dated February 11, 

2014. 

• Airbus Service Bulletin A320–22– 

1447, Revision 01, dated September 18, 

2014. 

• Airbus Service Bulletin A320–22– 

1461, Revision 04, dated September 15, 

2014. 

• Airbus Service Bulletin A320–31– 

1414, Revision 03, dated September 15, 

2014. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 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. 

Explanation of ‘‘RC’’ Procedures and 

Tests in Service Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The actions specified in the 

service information identified 

previously include procedures and tests 

that are identified as RC (required for 

compliance) because these procedures 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a NOTE under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests identified as RC 

must be done to comply with the 

proposed AD. However, procedures and 

tests that are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in a 

serviceable condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 953 airplanes of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

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11962 Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $243,015, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 6 work-hours (3 work-hours for an 

FWC and 3 work-hours for an FAC), for 

a cost of up to $510 per product. We 

have received no definitive data that 

would enable us to provide part cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

aircraft that might need these actions. 

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–2015–0251; 

Directorate Identifier 2014–NM–200–AD. 

(a) Comments Due Date 

We must receive comments by April 20, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) through (c)(4) of this AD, all 

manufacturer serial numbers. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 22, Auto flight; 31, 

Instruments. 

(e) Reason 

This AD was prompted by a determination 

that, in specific flight conditions, the 

allowable load limits on the vertical tail 

plane could be reached and possibly 

exceeded. Exceeding allowable load could 

result in detachment of the vertical tail plane. 

We are issuing this AD to prevent 

detachment of the vertical tail plane and 

consequent loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Pin Programming Modification 

Within 48 months after the effective date 

of this AD, modify the pin programming to 

activate the stop rudder input warning 

(SRIW) logic, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–22–1480, dated July 9, 

2014. 

(h) Inspection To Determine Part Numbers 

(P/Ns), Flight Warning Computer (FWC) and 

Flight Augmentation Computer (FAC) 

Replacement 

Prior to or concurrently with, the actions 

required by paragraph (g) of this AD: Inspect 

the part numbers of the FWC and the FAC 

installed on the airplane. If any FWC or FAC 

having a part number identified in paragraph 

(h)(1) or (h)(2) of this AD, as applicable, is 

installed on an airplane, prior to or 

concurrently with, the actions required by 

paragraph (g) of this AD, replace all affected 

FWCs and FACs with a unit having a part 

number identified in paragraph (h)(3) of this 

AD, in accordance with the Accomplishment 

Instructions of the applicable Airbus service 

bulletins specified in paragraph (i) of this 

AD. 

(1) Paragraphs (h)(1)(i) through (h)(1)(xvii) 

of this AD identify FWCs having part 

numbers that are non-compatible with the 

SRIW activation required by paragraph (g) of 

this AD. 

(i) 350E017238484 (H1D1). 

(ii) 350E053020303 (H2E3). 

(iii) 350E016187171 (C5). 

(iv) 350E053020404 (H2E4). 

(v) 350E017248685 (H1D2). 

(vi) 350E053020606 (H2F2). 

(vii) 350E017251414 (H1E1). 

(viii) 350E053020707 (H2F3). 

(ix) 350E017271616 (H1E2). 

(x) 350E053021010 (H2F3P). 

(xi) 350E018291818 (H1E3CJ). 

(xii) 350E053020808 (H2F4). 

(xiii) 350E018301919 (H1E3P). 

(xiv) 350E053020909 (H2–F5). 

(xv) 350E018312020 (H1E3Q). 

(xvi) 350E053021111 (H2–F6). 

(xvii) 350E053020202 (H2E2). 

(2) Paragraphs (h)(2)(i) through 

(h)(2)(xxxiv) of this AD identify FACs having 

part numbers that are non-compatible with 

the SRIW activation required by paragraph 

(g) of this AD. 

(i) B397AAM0202. 

(ii) B397BAM0101. 

(iii) B397BAM0512. 

(iv) B397AAM0301. 

(v) B397BAM0202. 

(vi) B397BAM0513. 

(vii) B397AAM0302. 

(viii) B397BAM0203. 

(ix) B397BAM0514. 

(x) B397AAM0303. 

(xi) B397BAM0305. 

(xii) B397BAM0515. 

(xiii) B397AAM0404. 

(xiv) B397BAM0406. 

(xv) B397BAM0616. 

(xvi) B397AAM0405. 

(xvii) B397BAM0407. 

(xviii) B397BAM0617. 

(xix) B397AAM0506. 

(xx) B397BAM0507. 

(xxi) B397BAM0618. 

(xxii) B397AAM0507. 

(xxiii) B397BAM0508. 

(xxiv) B397BAM0619. 

(xxv) B397AAM0508. 

(xxvi) B397BAM0509. 

(xxvii) B397BAM0620. 

(xxviii) B397AAM0509. 

(xxix) B397BAM0510. 

(xxx) B397CAM0101. 

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Federal Register / Vol. 80, No. 43 / Thursday, March 5, 2015 / Proposed Rules 11963 

(xxxi) B397AAM0510. 

(xxxii) B397BAM0511. 

(xxxiii) B397CAM0102. 

(xxxiv) Soft P/N G2856AAA01 installed on 

hard P/N C13206AA00. 

(3) Paragraphs (h)(3)(i) through (h)(3)(iv) of 

this AD identify the FWCs and FACs having 

the part numbers that are compatible with 

SRIW activation required by paragraph (g) of 

this AD. 

(i) For airplane configurations with no 

sharklet, an FAC having P/N B397BAM0621 

(621 hard B). 

(ii) For airplanes configured with sharklet 

A320 and A319, an FAC having P/N 

B397BAM0622 (622 hard B). 

(iii) For airplanes configured with sharklet 

A321, an FAC having P/N B397BAM0623 

(623 hard B). 

(iv) For all airplane configurations, an FAC 

having soft P/N G2856AAA02 installed on 

hard P/N C13206AA00 (CAA02 hard C) and 

FWC having P/N 350E053021212 (H2–F7). 

(i) Service Bulletins for Actions Required by 

Paragraph (h) of This AD 

Do the actions required by paragraph (h) of 

this AD in accordance with the 

Accomplishment Instructions of the 

applicable Airbus service bulletin specified 

in paragraphs (i)(1) through (i)(5) of this AD. 

(1) Airbus Service Bulletin A320–22–1375, 

dated January 15, 2014 (FAC 621 Hard B). 

(2) Airbus Service Bulletin A320–22–1427, 

Revision 04, dated February 11, 2014 (FAC 

622 Hard B). 

(3) Airbus Service Bulletin A320–22–1447, 

Revision 01, dated September 18, 2014 (FAC 

A02 Hard C). 

(4) Airbus Service Bulletin A320–22–1461, 

Revision 04, dated September 15, 2014 (FAC 

623 Hard B). 

(5) Airbus Service Bulletin A320–31–1414, 

Revision 03, dated September 15, 2014 (FWC 

H–F7). 

(j) Exclusion From Actions Required by 

Paragraphs (g) and (h) of This AD 

An airplane on which Airbus Modification 

154473 has been embodied in production is 

excluded from the requirements of 

paragraphs (g) and (h) of this AD, provided 

that, within 30 days after the effective date 

of this AD, an inspection of the part numbers 

of the FWC and the FAC installed on the 

airplane is done to determine that no FWC 

having a part number listed in paragraph 

(h)(1) of this AD, and no FAC having a part 

number part number listed in listed in 

paragraph (h)(2) of this AD, has been 

installed on that airplane since date of 

manufacture. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part numbers of the 

FWC and FAC can be conclusively 

determined from that review. If any FWC or 

FAC having a part number identified in 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable, is installed on a postmodification 154473 airplane: Within 30 

days after the effective date of this AD, do the 

replacement required by paragraph (h) of this 

AD. 

(k) Parts Installation Prohibitions 

After modification of an airplane as 

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

AD: Do not install on that airplane any FWC 

having a part number listed in paragraph 

(h)(1) of this AD or any FAC having a part 

number listed in paragraph (h)(2) of this AD. 

(l) Later Approved Parts 

Installation of a version (part number) of 

the FWC or FAC approved after the effective 

date of this AD is an approved method of 

compliance with the requirements of 

paragraph (h) or (j) of this AD, provided the 

requirements specified in paragraphs (l)(1) 

and (l)(2) of this AD are met. 

(1) The version (part number) must be 

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). 

(2) The installation must be accomplished 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(m) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (h) of this AD, if those 

actions were performed before the effective 

date of this AD using the Airbus service 

information identified in paragraphs (m)(1) 

through (m)(12) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Service Bulletin A320–22–1427, 

dated January 25, 2013. 

(2) Airbus Service Bulletin A320–22–1427, 

Revision 01, dated July 30, 2013. 

(3) Airbus Service Bulletin A320–22–1427, 

Revision 02, dated October 14, 2013. 

(4) Airbus Service Bulletin A320–22–1427, 

Revision 03, dated November 8, 2013. 

(5) Airbus Service Bulletin A320–22–1447, 

dated October 18, 2013. 

(6) Airbus Service Bulletin A320–22–1461, 

dated October 31, 2013. 

(7) Airbus Service Bulletin A320–22–1461, 

Revision 01, dated February 25, 2014. 

(8) Airbus Service Bulletin A320–22–1461, 

Revision 02, dated April 30, 2014. 

(9) Airbus Service Bulletin A320–22–1461, 

Revision 03, dated July 17, 2014. 

(10) Airbus Service Bulletin A320–31– 

1414, dated December 19, 2012. 

(11) Airbus Service Bulletin A320–31– 

1414, Revision 01, dated March 21, 2013. 

(12) Airbus Service Bulletin A320–31– 

1414, Revision 02, dated July 30, 2013. 

(n) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; 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) Required for Compliance (RC): If the 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(3) 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0217, dated 

September 26, 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–2015–0251. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 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 

19, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–04504 Filed 3–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

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