62072 Federal Register / Vol. 79, No. 200 / Thursday, October 16, 2014 / Proposed Rules 

Kidde Graviner: Docket No. FAA–2014– 

0751; Directorate Identifier 2013–NM– 

188–AD. 

(a) Comments Due Date 

We must receive comments by December 1, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Kidde Graviner handoperated fire extinguishers having part 

numbers 56412–001 (34H), 56411–001 (35H), 

and 56412–002 (38H). These fire 

extinguishers may be installed on, but not 

limited to, various transport and small 

airplanes, certificated in any category, 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

(c)(4), (c)(5), and (c)(6) of this AD. 

(1) BAE Systems (Operations) Limited 

Model ATP airplanes. 

(2) BAE Systems (Operations) Limited 

Model 4101 airplanes. 

(3) EADS CASA (Type Certificate 

previously held by Construcciones 

Aeronauticas, S.A.) Model C–212–CB, C– 

212–CC, C–212–CD, C–212–CE, C–212–CF, 

C–212–DE, and C–212–DF airplanes. 

(4) Fokker Services B.V. Model F.27 Mark 

050, 100, 200, 300, 400, 500, 600, and 700 

airplanes. 

(5) Short Brothers PLC Model SD3–60 

SHERPA, SD3–SHERPA, SD3–30, and SD3– 

60 airplanes. 

(6) SHORT BROTHERS & HARLAND LTD 

SC–7 Series 2 and SC–7 Series 3 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 26, Fire Protection. 

(e) Reason 

This AD was prompted by a report that a 

fire extinguisher failed to operate when the 

activation lever was pressed. We are issuing 

this AD to prevent fire extinguishers from 

failing to operate in the event of a fire, which 

could jeopardize occupants’ safety and 

continuation of safe flight and landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 6 months after the effective date of 

this AD, modify all Kidde Graviner handoperated fire extinguishers having part 

numbers 56412–001 (34H), 56411–001 (35H), 

and 56412–002 (38H), in accordance with the 

Accomplishment Instructions of Kidde 

Graviner Alert Service Bulletin A26–081, 

Revision 1, dated January 31, 2012. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

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

actions were performed before the effective 

date of this AD using Kidde Graviner Alert 

Service Bulletin A26–081, dated August 23, 

2011, which is not incorporated by reference 

in this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install any Kidde Graviner handoperated fire extinguisher having part 

number 56412–001 (34H), 56411–001 (35H), 

or 56412–002 (38H) on any airplane unless 

the fire extinguisher has been modified as 

specified in paragraph (g) of this AD. 

(j) Other FAA AD Provision 

The following provision for Alternative 

Methods of Compliances (AMOCs) also 

applies to this AD: The manager of the office 

having certificate responsibility for the 

affected product 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. The Manager, Boston Aircraft 

Certification Office (ACO), FAA, will 

coordinate requests for approval of AMOCs 

with the manager of the appropriate office for 

the affected product. Send information to 

ATTN: Caspar Wang, Aerospace Engineer, 

Boston Aircraft Certification Office (ACO), 

FAA, Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7799; fax: 781–238– 

7170; email: caspar.wang@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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2012–0037, dated 

March 9, 2012, 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–2014–0751. 

(2) For service information identified in 

this AD, contact Kidde Graviner Limited, 

Mathisen Way, Colnbrook, Slough, Berkshire, 

SL3 0HB, United Kingdom; telephone +44 (0) 

1753 583245; fax +44 (0) 1753 685040. 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 

September 23, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–24556 Filed 10–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0748; Directorate 

Identifier 2014–NM–013–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, and A321 

series airplanes; and Model A320–211, 

–212, –214, –231, –232, and –233 

airplanes. This proposed AD was 

prompted by reports of wear of the 

trimmable horizontal stabilizer actuator 

(THSA). This proposed AD would 

require repetitive inspections of the 

THSA for damage, and replacement if 

necessary; and replacement of the THSA 

after reaching a certain life limit. We are 

proposing this AD to detect and correct 

wear on the THSA, which would reduce 

the remaining life of the THSA, possibly 

resulting in premature failure and 

consequent reduced control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by December 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 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 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 79, No. 200 / Thursday, October 16, 2014 / Proposed Rules 62073 

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– 

0748; 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–2014–0748; Directorate Identifier 

2014–NM–013–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 2014–0011R1, 

dated January 17, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A318, A319, and 

A321 series airplanes and Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes. The MCAI states: 

In the frame of the A320 Extended Service 

Goal (ESG) project and the study on the 

Trimmable Horizontal Stabilizer Actuator 

(THSA), a sampling programme of in-service 

units has been performed and several cases 

of wear at different THSA levels were 

reported. 

This condition, if not detected and 

corrected, would reduce the remaining life of 

the THSA, possibly resulting in premature 

failure and consequent reduced control of the 

aeroplane. 

Prompted by these findings, Airbus issued 

Service Bulletin (SB) A320–27–1227 to 

provide THSA inspection instructions. 

For the reasons described above, this 

[EASA] AD requires repetitive inspections of 

the THSA and introduces a life limit for the 

THSA. 

The MCAI specifies a detailed 

inspection of the magnetic chip detector 

for metal particles, a spectrometric 

analysis of the oil drained from the 

THSA gearbox, a detailed inspection of 

the ballscrew and nut, and a detailed 

inspection of the upper and the lower 

attachments for damage. The corrective 

action is replacement of the THSA with 

a serviceable THSA. The compliance 

time for the THSA replacement ranges 

from before further flight to within 4 

months from drainage of the oil sample. 

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–2014– 

0748. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–27–1227, Revision 01, dated 

October 7, 2013. The actions described 

in this service information are intended 

to correct the unsafe condition 

identified in the MCAI. 

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. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

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62074 Federal Register / Vol. 79, No. 200 / Thursday, October 16, 2014 / Proposed Rules 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 

Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, the European 

Aviation Safety Agency (EASA), or 

Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature are not 

EASA-approved, unless EASA directly 

approves the manufacturer’s message or 

other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH. 

Costs of Compliance 

We estimate that this proposed AD 

affects 851 airplanes of U.S. registry. 

We also estimate that it would take 

about 6 work-hours per product to 

comply with the inspection 

requirements of this proposed AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost for the inspection specified in this 

proposed AD on U.S. operators to be 

$434,010, or $510 per product. 

We estimate that it would take about 

7 work-hours per product to comply 

with the actuator replacement 

requirements of this proposed AD. 

Required parts would cost about 

$240,000 per product. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost for 

the actuator replacement specified in 

this proposed AD on U.S. operators to 

be $204,746,345, or $240,595 per 

product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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–2014–0748; 

Directorate Identifier 2014–NM–013–AD. 

(a) Comments Due Date 

We must receive comments by December 1, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes, 

certificated in any category, identified in 

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

this AD, all manufacturer serial numbers. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

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

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by reports of wear 

of the trimmable horizontal stabilizer 

actuator (THSA). We are issuing this AD to 

detect and correct wear on the THSA, which 

would reduce the remaining life of the 

THSA, possibly resulting in premature 

failure and consequent reduced control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Inspections 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do a 

detailed inspection of the magnetic chip 

detector for metal particles, a spectrometric 

analysis of the oil drained from the THSA 

gearbox, a detailed inspection of the 

ballscrew and nut for damage (including, but 

not limited to, cracks, dents, corrosion, and 

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Federal Register / Vol. 79, No. 200 / Thursday, October 16, 2014 / Proposed Rules 62075 

unsatisfactory surface protection), and a 

detailed inspection of the upper and the 

lower attachments for damage (including, but 

not limited to, cracks, dents, corrosion, and 

unsatisfactory surface protection), in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1227, Revision 01, dated October 7, 2013. 

(1) Before the THSA accumulates 48,000 

total flight hours or 30,000 total flight cycles, 

whichever occurs first since first installation 

on an airplane. 

(2) Within 4 months after the effective date 

of this AD. 

(h) Repetitive Inspections 

Repeat the inspections required by 

paragraph (g) of this AD thereafter at 

intervals not to exceed the applicable time 

specified in paragraphs (h)(1) and (h)(2) of 

this AD. 

(1) For a THSA that, as of the date of the 

most recent inspection required by paragraph 

(g) of this AD, has accumulated less than 

67,500 total flight hours since first 

installation on an airplane: The repetitive 

inspection interval is 24 months. 

(2) For a THSA that, as of the date of the 

most recent inspection required by paragraph 

(g) of this AD, has accumulated 67,500 total 

flight hours or more since first installation on 

an airplane: The repetitive inspection 

interval is 4 months. 

(i) THSA Corrective Action 

If, during any inspection required by 

paragraphs (g) and (h) of this AD, any finding 

as described in Airbus Service Bulletin 

A320–27–1227, Revision 01, dated October 7, 

2013, is found: At the applicable compliance 

time (depending on the applicable findings) 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Airbus Service Bulletin A320–27–1227, 

Revision 01, dated October 7, 2013, replace 

the THSA with a serviceable THSA, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1227, Revision 01, dated October 7, 2013. 

For the purposes of this AD, a serviceable 

THSA is a THSA that has accumulated less 

than 67,500 total flight hours since first 

installation on an airplane. 

(j) THSA Replacement 

Before a THSA accumulates 67,500 total 

flight hours since first installation on an 

airplane, or within 12 months after the 

effective date of this AD, whichever occurs 

later: Replace the THSA with a serviceable 

THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1227, Revision 01, 

dated October 7, 2013. Thereafter, before the 

accumulation of 67,500 total flight hours 

since first installation on an airplane on any 

THSA, replace it with a serviceable THSA. 

(k) Replacement THSA: No Terminating 

Action 

Replacement of a THSA on an airplane, as 

required by paragraph (i) or (j) of this AD, 

does not constitute terminating action for the 

repetitive inspections required by paragraphs 

(g) and (h) of this AD for that airplane. After 

THSA replacement: At the applicable 

compliance time specified in paragraphs 

(g)(1), (g)(2), (h)(1), and (h)(2) of this AD, do 

the inspections required by paragraph (g) of 

this AD. 

(l) Replacement THSA Equivalency 

Repairs of a THSA in shop, as described in 

United Technologies Corporation Aerospace 

Systems Component Maintenance Manual 

27–44–51, are considered equivalent to 

having passed an inspection in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–27–1227, 

dated July 1, 2013; or Airbus Service Bulletin 

A320–27–1227, Revision 01, dated October 7, 

2013. Depending on the flight hours or flight 

cycles accumulated by the repaired THSA: At 

the applicable compliance time specified in 

paragraphs (g)(1), (g)(2), (h)(1), and (h)(2) of 

this AD, do the inspections required by 

paragraph (g) of this AD. 

(m) Parts Installation Limitation 

As of the effective date of this AD, 

installation on an airplane of a THSA that 

has accumulated 67,500 or more total flight 

hours is allowed, provided that, prior to 

installation, the THSA has been modified or 

inspected 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). 

(n) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraphs (g) and 

(h) of this AD, if those inspections were 

performed before the effective date of this AD 

using Airbus Service Bulletin A320–27–1227, 

dated July 1, 2013, which is not incorporated 

by reference in this AD. 

(o) 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) 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. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0011R1, dated January 17, 

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– 

2014–0748. 

(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 

September 23, 2014. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–24557 Filed 10–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0749; Directorate 

Identifier 2014–NM–051–AD] 

RIN 2120–AA64 

Airworthiness Directives; Lockheed 

Martin Corporation/Lockheed Martin 

Aeronautics Company 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 

Lockheed Martin Corporation/Lockheed 

Martin Aeronautics Company Model 

382, 382B, 382E, 382F, and 382G 

airplanes. This proposed AD was 

prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the upper and lower 

rainbow fittings on the outer wing are 

subject to widespread fatigue damage 

(WFD). This proposed AD would 

require repetitive inspections of the 

upper and lower rainbow fittings on the 

outer wing to detect cracks propagating 

from fasteners attaching the fittings to 

skin panels, and related investigative 

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