74726 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 

(l) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0038, dated 

March 4, 2015, 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– 

2015–6539. 

(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 

November 20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30216 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6541; Directorate 

Identifier 2015–NM–135–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

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 all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900, and –900ER series 

airplanes. This proposed AD was 

prompted by reports of a manufacturing 

oversight, in which a supplier omitted 

the required protective finish on certain 

bushings installed in the rear spar upper 

chord on horizontal stabilizers, which 

could lead to galvanic corrosion and 

consequent cracking of the rear spar 

upper chord. This proposed AD would 

require an inspection or records check 

to determine if affected horizontal 

stabilizers are installed, related 

investigative actions, and for affected 

horizontal stabilizers, repetitive 

inspections for any crack of the 

horizontal stabilizer rear spar upper 

chord, and corrective action if 

necessary. We are proposing this AD to 

detect and correct cracking of the rear 

spar upper chord, which can result in 

the failure of the upper chord and 

consequent departure of the horizontal 

stabilizer from the airplane, which can 

lead to loss of continued safe flight and 

landing. 

DATES: We must receive comments on 

this proposed AD by January 14, 2016. 

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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

6541. 

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– 

6541; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jason Deutschman, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6595; 

fax: 425–917–6590; email: 

jason.deutschman@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–6541; Directorate Identifier 2015– 

NM–135–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 because of 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 

We received reports of a 

manufacturing oversight, in which the 

required protective finish (zinc-nickel 

alloy plate or cadmium plate) was 

omitted on the 182A1508–4/–5/–6 

bushings (in line with the terminal 

fitting holes) installed in the rear spar 

upper chord on horizontal stabilizers 

with certain serial numbers. This issue 

was discovered after production of the 

affected stabilizers. 

The 182A1508–4/–5/–6 bushings are 

made from aluminum-nickel-bronze. 

Installing these bushings, without the 

required protective finish, into the 

2024–T3511 aluminum horizontal 

stabilizer rear spar upper chord can lead 

to galvanic corrosion between the 

dissimilar metals. Bushings with 

galvanic corrosion, if not corrected, can 

lead to cracking of the rear spar upper 

chord, which can result in the failure of 

the upper chord and consequent 

departure of the horizontal stabilizer 

from the airplane, which can lead to 

loss of continued safe flight and 

landing. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 737–55A1097, dated July 1, 

2015. The service information describes 

procedures for an inspection or records 

review to determine if affected 

horizontal stabilizers are installed, 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74727 

related investigative actions, high 

frequency eddy current inspections for 

any crack of the horizontal stabilizer 

rear spar upper chord, and corrective 

action if necessary. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary action, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

55A1097, dated July 1, 2015, specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

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 steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) The 

steps labeled as RC, including substeps 

under an RC step and any figures 

identified in an RC step, must be done 

to comply with the AD, and an AMOC 

is required for any deviations to RC 

steps, including substeps and identified 

figures; and (2) steps not labeled 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 RC steps, 

including substeps and identified 

figures, can still be done as specified, 

and the airplane can be put back in an 

airworthy condition. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,397 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspection or check .......................... 1 work-hour × $85 per hour = $85 ............................... $0 $85 $118,745 

We estimate the following costs to do 

any necessary inspections that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these inspections: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspections .................................................. 4 work-hours × $85 per hour = $340 ............................................ $0 $340 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs 

specified in this proposed AD. 

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. 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
74728 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 

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): 

The Boeing Company: Docket No. FAA– 

2015–6541; Directorate Identifier 2015– 

NM–135–AD. 

(a) Comments Due Date 

We must receive comments by January 14, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and 900ER series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by reports of a 

manufacturing oversight, in which a supplier 

omitted the required protective finish on 

certain bushings installed in the rear spar 

upper chord on horizontal stabilizers, which 

could lead to galvanic corrosion and 

consequent cracking of the rear spar upper 

chord. We are issuing this AD to detect and 

correct cracking of the rear spar upper chord, 

which can result in the failure of the upper 

chord and consequent departure of the 

horizontal stabilizer from the airplane, which 

can lead to loss of continued safe flight and 

landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Serial Number Check or Inspection To 

Determine If Certain Horizontal Stabilizers 

Are Installed, Related Investigative Actions, 

Repetitive Inspections for Cracks, and 

Corrective Action 

(1) Except as specified in paragraph (h)(1) 

of this AD, within the compliance time 

identified in paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Alert Service Bulletin 737– 

55A1097, dated July 1, 2015, do the actions 

specified in paragraph (g)(1)(i) or (g)(1)(ii) of 

this AD. 

(i) Do a records check to determine if an 

affected horizontal stabilizer is installed and 

if any horizontal stabilizer has been 

exchanged, and do all applicable related 

investigative actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–55A1097, dated July 1, 

2015. Affected horizontal stabilizers are 

identified in the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–55A1097, dated July 1, 2015. 

(ii) Do an inspection of the horizontal 

stabilizer identification plate to determine if 

any affected horizontal stabilizer is installed, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–55A1097, dated July 1, 2015. Affected 

horizontal stabilizers are identified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–55A1097, dated July 1, 

2015. 

(2) If, during any action required by 

paragraph (g)(1)(i) or (g)(1)(ii) of this AD, any 

affected horizontal stabilizer is found: Except 

as specified in paragraph (h)(1) of this AD, 

within the compliance time identified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 737–55A1097, dated 

July 1, 2015, do a high frequency eddy 

current (HFEC) inspection for any crack of 

the horizontal stabilizer rear spar upper 

chord and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–55A1097, dated July 1, 

2015, except as required by paragraph (h)(2) 

of this AD. Repeat the inspection thereafter 

at intervals identified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–55A1097, dated July 1, 2015. 

(h) Exceptions to the Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

737–55A1097, dated July 1, 2015, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 737–55A1097, dated 

July 1, 2015, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(i) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a horizontal stabilizer on 

any airplane, except as specified in 

paragraphs (i)(1) and (i)(2) of this AD. 

(1) A horizontal stabilizer may be installed 

if the part is inspected in accordance with 

‘‘Part 2: Horizontal Stabilizer Identification 

Plate Inspection’’ of the Accomplishments 

Instructions of Boeing Alert Service Bulletin 

737–55A1097, dated July 1, 2015, and no 

affected serial number is found. 

(2) A horizontal stabilizer may be installed 

if the part is inspected in accordance with 

‘‘Part 2: Horizontal Stabilizer Identification 

Plate Inspection’’ of the Accomplishments 

Instructions of Boeing Alert Service Bulletin 

737–55A1097, dated July 1, 2015, and an 

affected serial number is found, provided the 

actions specified in paragraphs (i)(2)(i) and 

(i)(2)(ii) of this AD are done, as applicable. 

(i) An initial HFEC inspection specified in 

paragraph (g)(2) of this AD is done before 

further flight and thereafter repetitive HFEC 

inspections specified in paragraph (g)(2) of 

this AD are done within the compliance 

times specified in paragraph (g)(2) of this AD. 

(ii) All applicable corrective actions are 

done before further flight as required by 

paragraph (h)(2) of this AD. 

(j) 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 (k) 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 the 

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 


jstallworth on DSK7TPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74729 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (j)(4)(i) and (j)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(k) Related Information 

(1) For more information about this AD, 

contact Jason Deutschman, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6595; fax: 425–917–6590; email: 

jason.deutschman@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, WA. For 

information on the availability of this 

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

Issued in Renton, Washington, on 

November 20, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–30223 Filed 11–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–6537; Directorate 

Identifier 2014–NM–154–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by reports of cracking 

of the aft fixed fairing (AFF) of the 

pylons due to fatigue damage of the 

structure. This proposed AD would 

require repetitive inspections for 

damage and cracking of the AFF of the 

pylons, and repair if necessary. We are 

proposing this AD to detect and correct 

damage and cracking of the AFF of the 

pylons, which could result in 

detachment of a pylon and consequent 

reduced structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by January 14, 2016. 

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—EAS, 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– 

6537; 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–2015–6537; Directorate Identifier 

2014–NM–154–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 2014–0154, dated July 2, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

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

condition for certain Airbus Model 

A318, A319, A320, and A321 series 

airplanes. The MCAI states: 

On aeroplanes equipped with post-mod 

33844 CFM pylons, several operators have 

reported cracks on the Aft Fixed Fairing 

(AFF). After material analysis, it appears that 

the pylon AFF structure, especially on this 

configuration, is subject to fatigue constraint 

damage which could lead to pylon AFF 

cracks. 

Further to these findings, Airbus released 

Alert Operators Transmission (AOT) 

A54N002–12 which provides instructions to 

inspect the pylon AFF, applicable only to 

aeroplanes incorporating Airbus production 

mod 33844 on CFM pylons. More recently, 

Airbus issued Service Bulletin (SB) A320– 

54–1027, superseding AOT A54N002–12. 

This condition, if not detected and 

corrected, could lead to detachment of a 

pylon AFF from the aeroplane, possibly 

resulting in injuries to persons on the 

ground. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DET) of the pylon AFF and, 

depending on findings, accomplishment of 

applicable corrective action(s). 


jstallworth on DSK7TPTVN1PROD with PROPOSALS