46902 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to GA 8 Airvan (Pty) Ltd 

Models GA8 and GA8–TC320 airplanes, 

certificated in any category, with a strut or 

strut fitting installed that has a part number 

and serial number listed in table 1 of 

GippsAero Service Bulletin SB–GA8–2017– 

174, Issue 2, dated May 23, 2018 (GippsAero 

SB–GA8–2017–174, Issue 2). 

(d) Subject 

Air Transport Association of America 

(ATA) Code 57: Wings. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as certain 

wing strut fittings manufactured with 

incorrect grain orientation, which has an 

unknown effect on fatigue-related concerns. 

We are issuing this AD to detect and address 

fatigue-related damage to the wing strut 

fittings, which could lead to failure of the 

wing with consequent loss of control of the 

airplane. 

(f) Actions and Compliance 

Unless already done, do the following 

actions in paragraphs (f)(1) through (6) of this 

AD: 

(1) Within 3 months after the effective date 

of this AD or within 100 hours time-inservice (TIS) after the effective date of this 

AD, whichever occurs first, with the wing 

struts removed, visually inspect each forward 

and aft wing strut fitting and fuselage 

attachment point for cracks, corrosion, and 

damage. If a crack, corrosion, or damage is 

found during the inspection, before further 

flight, do the applicable corrective actions 

(check torque, restore surface protection, 

rework areas with fouling, and replace any 

part with a crack, corrosion, or damage). 

Follow the procedures in Parts C1, C2, and 

D or E, as applicable, in the Accomplishment 

Instructions in GippsAero SB–GA8–2017– 

174, Issue 2. 

(2) Within 3 months after the effective date 

of this AD or within 100 hours TIS after the 

effective date of this AD, whichever occurs 

first, and thereafter at intervals not to exceed 

100 hours TIS, visually inspect each strut 

and strut fitting for cracks, corrosion, and 

damage. If a crack, corrosion, or damage is 

found during any of the inspections, before 

further flight, do the applicable corrective 

actions (check torque, restore surface 

protection, and replace any part with a crack, 

corrosion, or damage). Follow the procedures 

in Parts B and D or E, as applicable, in the 

Accomplishment Instructions of GippsAero 

SB–GA8–2017–174, Issue 2. 

(3) Within 1,000 hours TIS after doing the 

inspections required in paragraph (f)(1) of 

this AD and thereafter at intervals not to 

exceed 1,000 hours TIS, with the wing struts 

installed, visually inspect each forward and 

aft wing strut, strut fitting, and strut fitting 

lug hole for cracks, corrosion, and damage. If 

a crack, corrosion, or damage is found during 

any of the inspections, before further flight, 

do the applicable corrective actions (do 

additional inspections, replace hardware, 

and replace any part with a crack, corrosion, 

or damage). Follow the procedures in Parts 

C3 and D or E, as applicable, in the 

Accomplishment Instructions of GippsAero 

SB–GA8–2017–174, Issue 2. 

(4) To use an eddy current or fluorescent 

liquid penetrant inspection method instead 

of a visual inspection for the requirements in 

paragraphs (f)(1) of this AD, the Manager, 

Small Airplane Standards Branch, FAA must 

approve your inspection method, and the 

Manager’s approval letter must specifically 

refer to this AD. Send your approval request 

to the contact information found in 

paragraph (g)(1) of this AD. 

(5) Remove from service each part listed in 

Parts D and E of table 3 on or before the part 

exceeds its specified replacement time and 

replace with an airworthy part. On the 

effective date of this AD, any part listed in 

table 3 of GippsAero SB–GA8–2017–174, 

Issue 2, that has exceeded its replacement 

time, within 100 hours TIS after the effective 

date of this AD or within 12 months after the 

effective date of this AD, whichever occurs 

first, remove the part from service and 

replace with an airworthy part. Follow the 

replacement procedures in Part D or Part E, 

as applicable, in the Accomplishment 

Instructions of GippsAero SB–GA8–2017– 

174, Issue 2. 

(6) Within 24 hours after each inspection 

required in paragraphs (f)(1) and (2) of this 

AD, submit a report of the inspection results, 

even if no damage is found, to the Civil 

Aviation Safety Authority (CASA) and GA 8 

Airvan (Pty) Ltd. Use the Document 

Compliance Notice of GippsAero SB–GA8– 

2017–174, Issue 2, and include in the report 

the total hours TIS on the airplane and the 

type of operation. You may use the contact 

information found in paragraph (h) of this 

AD to contact GA 8 Airvan (Pty) Ltd. To 

contact CASA, use the online CASA Defect 

Reporting Service at the following internet 

address: https://drs.casa.gov.au/. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Small Airplane 

Standards Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Standards Branch, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

instead be accomplished using a method 

approved by the Manager, Small Airplane 

Standards Branch, FAA; or CASA. 

(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 currently 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0731. Public reporting for 

this collection of information is estimated to 

be approximately 1 hour per response, 

including the time for reviewing instructions, 

searching existing data sources, gathering 

and maintaining the data needed, completing 

and reviewing the collection of information. 

All responses to this collection of 

information are voluntary; the nature and 

extent of confidentiality to be provided, if 

any. Send comments regarding this burden 

estimate or any other aspect of this collection 

of information, including suggestions for 

reducing this burden to: Information 

Collection Clearance Officer, Federal 

Aviation Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

(h) Related Information 

Refer to MCAI issued by CASA, AD No. 

AD/GA8/9, Amendment 1, dated May 29, 

2018. You may examine the MCAI on the 

internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2018–0771. For service information related to 

this AD, contact GA 8 Airvan (Pty) Ltd, c/o 

GippsAero Pty Ltd, Attn: Technical Services, 

P.O. Box 881, Morwell Victoria 3840, 

Australia; telephone: +61 03 5172 1200; fax: 

+61 03 5172 1201; email: aircraft.techpubs@

mahindraaerospace.com. You may review 

this referenced service information at the 

FAA, Policy and Innovation Division, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on August 

31, 2018. 

Melvin J. Johnson, 

Deputy Director, Policy & Innovation Division, 

Aircraft Certification Service. 

[FR Doc. 2018–19889 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0793; Product 

Identifier 2018–NM–057–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46903 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This proposed AD was 

prompted by a report of cracks in the 

body station (STA) 303.9 frame web and 

doubler at fastener holes common to the 

stop fitting at stringer 16 left (S–16L). 

This proposed AD would require 

repetitive surface high frequency eddy 

current (HFEC) inspections for cracking 

of the STA 303.9 frame web and doubler 

at the stop fitting at S–16L, and 

applicable on-condition actions. We are 

proposing this AD to address the unsafe 

condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 1, 2018. 

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 NPRM, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110–SK57, Seal Beach, CA 

90740–5600; phone: 562–797–1717; 

internet: https://www.myboeingfleet.

com. You may view this referenced 

service information at the FAA, 

Transport Standards Branch, 2200 

South 216th St., Des Moines, WA. For 

information on the availability of this 

material at the FAA, call 206–231–3195. 

It is also available on the internet at 

http://www.regulations.gov by searching 

for and locating Docket No. FAA–2018– 

0793. 

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–2018– 

0793; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Galib Abumeri, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles 

ACO Branch, 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5324; fax: 562–627– 

5210; email: galib.abumeri@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– 

2018–0793; Product Identifier 2018– 

NM–057–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 

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 have received a report indicating 

cracks in the STA 303.9 frame web and 

doubler at fastener holes common to the 

stop fitting at S–16L. The cracks were 

found during accomplishment of Boeing 

Service Bulletin 737–53A1188. We have 

determined that the existing inspection 

programs are not sufficient to find any 

crack in the STA 303.9 frame web and 

doubler at the stop fitting at S–16L. This 

condition, if not addressed, could result 

in the inability of a principal structural 

element to sustain limit loads and 

possible rapid decompression of the 

airplane. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Requirements 

Bulletin 737–53A1375 RB, dated March 

12, 2018. The service information 

describes procedures for repetitive 

surface HFEC inspections for cracking of 

the STA 303.9 frame web and doubler 

at the stop fitting at S–16L, and 

applicable on-condition actions. 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. 

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 

accomplishment of the actions 

identified in Boeing Requirements 

Bulletin 737–53A1375 RB, dated March 

12, 2018, described previously, except 

for any differences identified as 

exceptions in the regulatory text of this 

proposed AD. 

For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2018– 

0793. 

Explanation of Applicability 

Model 737 airplanes having line 

numbers 1 through 291 have a limit of 

validity (LOV) of 34,000 total flight 

cycles, and the actions proposed in this 

NPRM, as specified in Boeing 

Requirements Bulletin 737–53A1375 

RB, dated March 12, 2018, would be 

required at a compliance time occurring 

after that LOV. Although operation of an 

airplane beyond its LOV is prohibited 

by 14 CFR 121.1115 and 129.115, this 

NPRM would include those airplanes in 

the applicability so that these airplanes 

are tracked in the event the LOV is 

extended in the future. 

Explanation of Requirements Bulletin 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement is a process for annotating 

which steps in the service information 

are ‘‘required for compliance’’ (RC) with 

an AD. Boeing has implemented this RC 

concept into Boeing service bulletins. 

In an effort to further improve the 

quality of ADs and AD-related Boeing 

service information, a joint process 

improvement initiative was worked 

between the FAA and Boeing. The 

initiative resulted in the development of 

a new process in which the service 

information more clearly identifies the 

actions needed to address the unsafe 

condition in the ‘‘Accomplishment 

Instructions.’’ The new process results 

in a Boeing Requirements Bulletin, 

which contains only the actions needed 

to address the unsafe condition (i.e., 

only the RC actions). 


daltland on DSKBBV9HB2PROD with PROPOSALS
46904 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 

Costs of Compliance 

We estimate that this proposed AD 

affects 67 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

HFEC Inspections ........ 13 work-hours × $85 per hour = 

$1,105 per inspection cycle.

$0 $1,105 per inspection cycle .... $74,035 per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes and associated 

appliances to the Director of the System 

Oversight Division. 

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– 

2018–0793; Product Identifier 2018– 

NM–057–AD. 

(a) Comments Due Date 

We must receive comments by November 

1, 2018. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks in the body station (STA) 303.9 frame 

web and doubler at fastener holes common 

to the stop fitting at stringer 16 left (S–16L). 

We are issuing this AD to address cracks in 

the STA 303.9 frame web and doubler at the 

stop fitting at S–16L, which, if not addressed, 

could result in the inability of a principal 

structural element to sustain limit loads and 

possible rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions for Group 1 

For airplanes identified as Group 1 in 

Boeing Requirements Bulletin 737–53A1375 

RB, dated March 12, 2018: Within 120 days 

after the effective date of this AD, inspect the 

airplane and do all applicable on-condition 

actions using a method approved in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(h) Required Actions for Groups 2 

Through 5 

Except as specified in paragraph (i) of this 

AD: For airplanes identified as Groups 2 

through 5 in Boeing Requirements Bulletin 

737–53A1375 RB, dated March 12, 2018, at 

the applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing 

Requirements Bulletin 737–53A1375 RB, 

dated March 12, 2018, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Requirements Bulletin 737–53A1375 RB, 

dated March 12, 2018. 

Note 1 to paragraph (h) of this AD: 

Guidance for accomplishing the actions 

required by this AD can be found in Boeing 

Alert Service Bulletin 737–53A1375, dated 

March 12, 2018, which is referred to in 

Boeing Requirements Bulletin 737–53A1375 

RB, dated March 12, 2018. 

(i) Exceptions to Service Information 

Specifications 

(1) For purposes of determining 

compliance with the requirements of this AD: 

Where Boeing Requirements Bulletin 737– 

53A1375 RB, dated March 12, 2018, uses the 

phrase ‘‘the original issue date of 

Requirements Bulletin 737–53A1375 RB,’’ 

this AD requires using ‘‘the effective date of 

this AD.’’ 

(2) Where Boeing Requirements Bulletin 

737–53A1375 RB, dated March 12, 2018, 

specifies contacting Boeing for repair 

instructions, this AD requires repair using a 

method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 


daltland on DSKBBV9HB2PROD with PROPOSALS
Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46905 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles ACO Branch, 

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 

certification office, send it to the attention of 

the person identified in paragraph (k)(1) of 

this AD. Information may be emailed to: 

9-ANM-LAACO-AMOC-Requests@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, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO Branch, FAA, to make those findings. 

To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Galib Abumeri, Aerospace Engineer, 

Airframe Section, FAA, Los Angeles ACO 

Branch, 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5324; fax: 562–627–5210; email: 

galib.abumeri@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster Blvd., 

MC 110–SK57, Seal Beach, CA 90740–5600; 

phone: 562–797–1717; internet: https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Standards Branch, 2200 South 

216th St., Des Moines, WA. For information 

on the availability of this material at the 

FAA, call 206–231–3195. 

Issued in Des Moines, Washington, on 

August 30, 2018. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2018–19840 Filed 9–14–18; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2018–0795; Product 

Identifier 2018–NM–076–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–20– 

04, which applies to all Airbus SAS 

Model A318 series airplanes; Airbus 

SAS Model A319 series airplanes; 

Airbus SAS Model A320–111, –211, 

–212, –214, –231, –232, and –233 

airplanes; and Airbus SAS Model A321– 

111, –112, –131, –211, –212, –213, –231, 

and –232 airplanes. AD 2014–20–04 

requires repetitive inspections for 

cracking of the four titanium angles 

between the belly fairing and the keel 

beam side panel, an inspection for 

cracking of the open holes if any 

cracking is found in the titanium angles, 

and repair or replacement if necessary. 

Since we issued AD 2014–20–04, we 

have determined that additional work is 

necessary for certain airplanes. This 

proposed AD would continue to require 

repetitive inspections for cracking of the 

four titanium angles between the belly 

fairing and the keel beam side panel, an 

inspection for cracking of the open 

holes if any cracking is found in the 

titanium angles, and repair or 

replacement if necessary. This proposed 

AD would also revise the applicability 

by adding Model A320–216 airplanes. 

This proposed AD would also require a 

detailed inspection for and replacement 

of certain rivets (including a rotating 

probe test for cracks in the open holes), 

and corrective actions if necessary. We 

are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by November 1, 2018. 

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 NPRM, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; phone: +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 

Standards Branch, 2200 South 216th St., 

Des Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. 

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–2018– 

0795; or in person at Docket Operations 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The AD docket contains this NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for Docket Operations 

(phone: 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 Section, Transport 

Standards Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

phone and fax 206–231–3223. 

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– 

2018–0795; Product Identifier 2018– 

NM–076–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 

We issued AD 2014–20–04, 

Amendment 39–17977 (79 FR 59636, 


daltland on DSKBBV9HB2PROD with PROPOSALS