Document ID: FAA-2018-0771-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: GA 8 Airvan (Pty) Ltd Airplanes
Posted Date: 2019-04-18T04:00Z

[Federal Register Volume 84, Number 75 (Thursday, April 18, 2019)]
[Rules and Regulations]
[Pages 16202-16205]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-07702]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0771; Product Identifier 2018-CE-029-AD; Amendment 
39-19619; AD 2019-07-08]
RIN 2120-AA64

Airworthiness Directives; GA 8 Airvan (Pty) Ltd Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for GA 8 
Airvan (Pty) Ltd Model GA8 and Model GA8-TC320 airplanes. This AD 
results from mandatory continuing airworthiness information (MCAI) 
issued 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 AD to require actions to address 
the unsafe condition on these products.

DATES: This AD is effective May 23, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 23, 2019.

ADDRESSES: 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, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
    For service information identified in 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: [email protected]. 
You may view 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. It is also available on the internet at http://www.regulations.gov by searching for Docket No. FAA-2018-0771.

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: 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to GA 8 Airvan (Pty) Ltd Model 
GA8 and Model GA8-TC320 airplanes. The NPRM was published in the 
Federal Register on September 17, 2018 (83 FR 46900). The NPRM proposed 
to correct an unsafe condition for the specified products and was based 
on mandatory continuing airworthiness information (MCAI) originated by 
the Civil Aviation Safety Authority (CASA), which is the aviation 
authority of the Commonwealth of Australia. 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 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.

The MCAI can be found in the AD docket on the internet at: https://www.regulations.gov/document?D=FAA-2018-0771-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or

[[Page 16203]]

on the determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed GippsAero 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.

Costs of Compliance

    We estimate that this 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 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 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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 AD:
    (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.

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 
the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2019-07-08 GA 8 Airvan (Pty) Ltd: Amendment 39-19619; Docket No. 
FAA-2018-0771; Product Identifier 2018-CE-029-AD.

[[Page 16204]]

(a) Effective Date

    This AD becomes effective May 23, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to GA 8 Airvan (Pty) Ltd Model GA8 and Model 
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 (7) of this AD:
    (1) Within 3 months after May 23, 2019 (the effective date of 
this AD) or within 100 hours time-in-service (TIS) after May 23, 
2019 (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 there is a crack, any corrosion, or any damage, 
before further flight, do the applicable corrective actions 
(including checking torque, restoring surface protection, reworking 
areas with fouling, and replacing 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 May 23, 2019 (the effective date of 
this AD) or within 100 hours TIS after May 23, 2019 (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 there is a 
crack, any corrosion, or any damage, before further flight, do the 
applicable corrective actions (including checking torque, restoring 
surface protection, and replacing 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 there is a 
crack, any corrosion, or any damage, before further flight, do the 
applicable corrective actions (including additional inspections, 
replacing hardware, and replacing 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 paragraph (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) As of May 23, 2019 (the effective date of this AD), remove 
from service each part on or before exceeding its replacement time 
listed in Parts D and E of table 3 of GippsAero SB-GA8-2017-174, 
Issue 2, and replace with an airworthy part by following the 
procedures in Part D or Part E, as applicable, in the Accomplishment 
Instructions of GippsAero SB-GA8-2017-174, Issue 2.
    (6) For each part that has, on May 23, 2019 (the effective date 
of this AD), exceeded its replacement time listed in Parts D and E 
of table 3 of GippsAero SB-GA8-2017-174, Issue 2, you may comply 
with the requirements in paragraph (f)(5) of this AD within 100 
hours TIS after May 23, 2019 (the effective date of this AD) or 
within 12 months after May 23, 2019 (the effective date of this AD), 
whichever occurs first.
    (7) Within 24 hours after each inspection required in paragraphs 
(f)(1) and (2) of this AD, submit a report of the inspection results 
as specified in the Document Compliance Notice of GippsAero SB-GA8-
2017-174, Issue 2, even if no damage is found, to the Civil Aviation 
Safety Authority (CASA) and GA 8 Airvan (Pty) Ltd. Also 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 
(i)(3) 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: [email protected]. 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.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) GippsAero Service Bulletin SB-GA8-2017-174, Issue 2, dated 
May 23, 2018 (ii) [Reserved]
    (3) For service information identified in 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: 
[email protected].
    (4) You may view this 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. In addition, you can access this service information 
on the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0771.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records

[[Page 16205]]

Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Kansas City, Missouri, on April 5, 2019.
Melvin J. Johnson,
Deputy Director, Policy & Innovation Division, Aircraft Certification 
Service.
[FR Doc. 2019-07702 Filed 4-17-19; 8:45 am]
 BILLING CODE 4910-13-P