46900 Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 

(ii) Reserved. 

(h) Definition 

For the purpose of this AD, an ‘‘engine 

shop visit’’ is the induction of an engine into 

the shop for maintenance involving the 

separation of pairs of major mating engine 

flanges, or any removal of the RGB assembly. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, ECO 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 (j)(1) of this AD. You 

may email your request to: ANE-AD-AMOC@

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. 

(j) Related Information 

(1) For more information about this AD, 

contact Barbara Caufield, Aerospace 

Engineer, ECO Branch, FAA, 1200 District 

Avenue, Burlington, MA 01803; phone: 781– 

238–7146; fax: 781–238–7199; email: 

barbara.caufield@faa.gov. 

(2) Refer to Transport Canada AD CF– 

2015–01R1, dated November 18, 2016, for 

more information. You may examine the 

Transport Canada AD in the AD docket on 

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

searching for and locating it in Docket No. 

FAA–2018–0739. 

(3) For service information identified in 

this AD, contact Pratt & Whitney Canada 

Corp., 1000 Marie-Victorin, Longueuil, 

Quebec, Canada J4G 1A1; phone: 800–268– 

8000; fax: 450–647–2888; website: http://

www.pwc.ca. You may view this service 

information at the FAA, Engine & Propeller 

Standards Branch, 1200 District Avenue, 

Burlington, MA 01803. For information on 

the availability of this material at the FAA, 

call 781–238–7759. 

Issued in Burlington, Massachusetts, on 

September 7, 2018. 

Robert J. Ganley, 

Manager, Engine & Propeller Standards 

Branch, Aircraft Certification Service. 

[FR Doc. 2018–19862 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–2018–0771; Product 

Identifier 2018–CE–029–AD] 

RIN 2120–AA64 

Airworthiness Directives; GA 8 Airvan 

(Pty) Ltd Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for GA 8 

Airvan (Pty) Ltd Models GA8 and GA8– 

TC320 airplanes. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an 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 proposed AD to require 

actions 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 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 20590, 

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

through Friday, except Federal holidays. 

For service information identified in 

this proposed 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. 

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– 

0771; 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 proposed 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for 

Docket Operations (telephone (800) 

647–5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

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. 

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–2018–0771; Product Identifier 

2018–CE–029–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://

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 Civil Aviation Safety Authority 

(CASA), which is the aviation authority 

for Australia, has issued AD No. AD/ 

GA8/9, Amendment 1, dated May 29, 

2018 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Amendment 1 of this [CASA] AD is issued 

to amend the replacement times as Service 

Bulletin GA8–2017–174 Issue 2 changed the 

mandatory replacement times for part 

number GA8–570026–035 strut from 6000 

hours time in service or 3 calendar years to 

9000 hours time in service or 5 calendar 

years, whichever occurs first. 

A manufacturing quality escape has 

resulted in wing strut fittings in the effective 

serial number range to be manufactured with 


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Federal Register / Vol. 83, No. 180 / Monday, September 17, 2018 / Proposed Rules 46901 

incorrect grain orientation. The fatigue 

implications of the incorrect grain are not 

well understood. Therefore, CASA has 

mandated a conservative factored fatigue life 

limit based on the known fleet data of the 

affected aircraft. CASA will continue to 

gather data for the purposes of managing the 

fleet removal of these fittings from service. 

You may examine the MCAI on the 

internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2018–0771. 

Related Service Information Under 1 

CFR Part 51 

GippsAero has issued Service Bulletin 

SB–GA8–2017–174, Issue 2, dated May 

23, 2018. The service information 

describes procedures for wing strut and 

strut fitting inspection and replacement. 

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 and Requirements 

of the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 50 airplanes of U.S. 

registry. The average labor rate is $85 

per work-hour. 

We estimate that it would take about 

8 work-hours and $200 for parts to do 

the initial inspections of this proposed 

AD, for a cost of $880 per airplane and 

$44,000 for the U.S. operator fleet. We 

estimate that it would take about 5 

work-hours and $200 for parts to do the 

repetitive inspections, for a cost of $625 

per airplane and $31,250 for the U.S. 

operator fleet per inspection cycle. 

In addition, we estimate that 

replacing the struts and strut fittings 

would take about 10 work-hours and 

require parts costing $7,000, for a cost 

of $7,850 per airplane and $392,500 for 

the U.S. operator fleet. 

Reporting the inspection findings 

would require about 1 work-hour, for a 

cost of $85 per airplane and $4,250 for 

the U.S. operator fleet per inspection 

cycle. 

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. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to 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 2120–0056. 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 mandatory as required 

by this AD; 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. 

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 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 small airplanes, gliders, 

balloons, airships, domestic business jet 

transport airplanes, and associated 

appliances to the Director of the Policy 

and Innovation 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): 

GA 8 Airvan (Pty) Ltd: Docket No. FAA– 

2018–0771; Product Identifier 2018–CE– 

029–AD. 

(a) Comments Due Date 

We must receive comments by November 

1, 2018. 


daltland on DSKBBV9HB2PROD with PROPOSALS
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). 


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