This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

4211 

Vol. 89, No. 15 

Tuesday, January 23, 2024 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0035; Project 

Identifier MCAI–2023–00986–A] 

RIN 2120–AA64 

Airworthiness Directives; GA 8 Airvan 

(Pty) Ltd Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede Airworthiness Directive (AD) 

2010–18–06, which applies to all GA8 

Airvan (Pty) Ltd Model GA8 and GA8– 

TC320 airplanes. AD 2010–18–06 

requires inspections and a minor design 

change to the forward slide of the cargo 

door with corrective action as necessary. 

Since the FAA issued AD 2010–18–06, 

the Civil Aviation Safety Authority 

(CASA), which is the aviation authority 

for Australia, superseded the previous 

CASA Australia AD to incorporate more 

detailed inspections and additional 

modifications as specified in updated 

service information published by the 

manufacturer. This proposed AD was 

prompted by reports of in-flight cargo 

door separation. This proposed AD 

would require inspections and rework 

(modifications) of the cargo door with 

corrective action as necessary. The FAA 

is proposing this AD to address the 

unsafe condition on these products. 

DATES: The FAA must receive comments 

on this NPRM by March 8, 2024. 

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 

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. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0035; 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 mandatory 

continuing airworthiness information 

(MCAI) any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

Material Incorporated by Reference: 

• For service information identified 

in this NPRM, contact GA8 Airvan (Pty) 

Ltd, PO Box 881, Morwell, Victoria 

3840, Australia; phone: +61 03 5172 

1200; website: gippsaero.com.au; email: 

TECHPUBS@gippsaero.com.au. 

• You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 901 Locust, Kansas City, MO 

64106. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

(816) 329–4059; email: doug.rudolph@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2024–0035; Project Identifier 

MCAI–2023–00986–A’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend the proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Doug Rudolph, 

Aviation Safety Engineer, FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590. Any commentary that the 

FAA receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The FAA issued AD 2010–18–06, 

Amendment 39–16419 (75 FR 52253, 

August 25, 2010) (AD 2010–18–06), for 

all GA8 Airvan (Pty) Ltd Model GA8 

and GA8–TC320 airplanes. AD 2010– 

18–06 was prompted by MCAI 

originated by CASA, which is the 

aviation authority for Australia. CASA 

Australia issued CASA Australia AD 

AD/GA8/3 Amdt 2, dated August 11, 

2010 (CASA Australia AD/GA8/3 Amdt 

2) to correct an unsafe condition 

identified as excessive wear in the 

forward cargo door slide, which could 

result in an in-flight separation of the 

cargo door, with possible loss of control 

of the airplane. CASA Australia AD AD/ 

GA8/3 Amdt 2 was issued to require the 

actions in service information updated 

by the manufacturer to remove any 

ambiguities in the previous revision and 

provide an improved inspection method 

and a minor design change to the 

forward slide of the cargo door 

(inclusion of a slide backing plate, 

castellated nut, and split pin). 

AD 2010–18–06 requires doing all of 

Action 1 (measuring the groove width of 


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the forward cargo door slide and if it 

exceeds 0.145 inch at any point along 

the slide, or is cracked, installing a new 

slider assembly) and Action 2 

(inspecting wear of the forward slide of 

the cargo door and doing applicable 

corrective action steps specified in 

Action 1) of GippsAero Pty. Ltd. 

Mandatory Service Bulletin SB–GA8– 

2005–23, Issue 3, dated August 5, 2010. 

The FAA issued AD 2010–18–06 to 

address excessive wear in the forward 

cargo door slide. 

Actions Since AD 2010–18–06 Was 

Issued 

Since the FAA issued AD 2010–18– 

06, CASA Australia superseded CASA 

Australia AD AD/GA8/3 Amdt 2 and 

issued CASA Australia AD AD/GA8/3 

Amdt 3, dated August 18, 2023 (CASA 

Australia AD AD/GA8/3 Amdt 3) (also 

referred to as the MCAI). The MCAI 

states that inspections revealed cases of 

excessive wear in the forward slide of 

the cargo door. Excessive wear in the 

forward slide of the cargo door may 

result in the cargo door separating from 

the airplane in flight with potentially 

catastrophic results. The MCAI requires 

accomplishing the actions specified in 

GippsAero Service Bulletin SB–GA8– 

2005–23, Issue 7, dated May 30, 2023 

(GippsAero Service Bulletin SB–GA8– 

2005–23, Issue 7). This service bulletin 

includes procedures for revised 

inspections of the door mechanism, 

installing a stop on the forward slide of 

the cargo door and reworking the door 

slide to suit (accommodate) the track 

stop installation. Depending on the 

findings of the inspections, additional 

actions might be necessary including 

reworking the door mechanism pivot, 

upgrading the door operating rod, or 

fitting a door handle with an integral 

stop. 

The FAA is proposing this AD to 

address excessive wear in the forward 

slide of the cargo door. The unsafe 

condition, if not addressed, could result 

in the cargo door separating from the 

airplane during flight, with potential 

loss of control of the airplane. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2024–0035. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed GippsAero Service 

Bulletin SB–GA8–2005–23, Issue 8, 

dated October 11, 2023 (GippsAero SB– 

GA8–2005–23, Issue 8). This service 

information specifies procedures for 

installing a backing plate on the forward 

slide of the cargo door; inspecting the 

forward slide of the cargo door for 

excessive wear; inspecting the cargo 

door latching mechanism for contact 

between the operating rod and door 

handle pivot post, inspecting the 

threaded studs and rod ends at both 

ends of the operating rod for bending, 

and checking the cargo door handle 

engagement with the catch; reworking 

the cargo door handle pivot post; 

reworking the door operating rod; 

inspecting the door handle to determine 

if an integrated stop is installed and 

checking for excessive play; and 

inspecting the center rail of the cargo 

door to determine if an aft stop is 

installed, installing an aft stop, and 

reworking the center rail of the cargo 

door to accommodate the track stop. 

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 ADDRESSES. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country and are approved for operation 

in the United States. Pursuant to the 

FAA’s bilateral agreement with this 

State of Design Authority, it has notified 

the FAA of the unsafe condition 

described in the MCAI and service 

information referenced above. The FAA 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would retain none 

of the requirements of AD 2010–18–06. 

This proposed AD would require 

accomplishing the actions specified in 

the service information already 

described, except as discussed under 

‘‘Differences Between this Proposed AD 

and the MCAI.’’ 

Differences Between This Proposed AD 

and the MCAI 

The MCAI applicability is Gippsland 

Aeronautics Model GA8 Series 

airplanes, all serial numbers. The 

applicability in this proposed AD would 

be GA8 Airvan (Pty) Ltd Model GA8 and 

GA8–TC320 airplanes because the FAA 

type certificate specifies GA8 Airvan 

(Pty) Ltd instead of Gippsland 

Aeronautics and specifies Model GA8 

and GA8–TC320 airplanes instead of 

Model GA8 Series airplanes. 

The MCAI requires doing the actions 

in Gippsland Aeronautics mandatory 

service bulletin SB–GA8–2005–23 Issue 

7, dated May 30, 2023. This proposed 

AD would require doing the actions in 

GippsAero SB–GA8–2005–23, Issue 8. 

After the MCAI was published, the 

manufacturer issued GippsAero SB– 

GA8–2005–23, Issue 8, which was 

revised to provide clarification 

regarding the actions and compliance 

schedule. The title page of GippsAero 

SB–GA8–2005–23, Issue 8, specifies 

GippsAero instead of Gippsland 

Aeronautics. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 61 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD. 

The corresponding letter and number in 

parenthesis refer to the specific 

paragraph in GippsAero SB–GA8–2005– 

23, Issue 8. 

ESTIMATED COSTS

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

Installing forward cargo door 

slide backing plate (A1).

0.50 work-hour × $85 per 

hour = $42.50.

$175 $217.50 .................................. $13,267.50. 

Inspecting forward cargo door 

slide wear (A2).

0.25 work-hour × $85 per 

hour = $21.25 per inspection cycle.

0 21.25 per inspection cycle ..... 1,296.25 per inspection cycle. 

Inspecting cargo door latching 

mechanism (B1).

1 work-hour × $85 per hour = 

$85 per inspection cycle.

0 85 per inspection cycle .......... 5,185 per inspection cycle. 

Inspecting cargo door handle 

and inspecting for excessive play (C).

0.75 work-hour × $85 per 

hour = $63.75.

0 63.75 ...................................... 3,88.75. 


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ESTIMATED COSTS—Continued 

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

Inspecting cargo door center 

rail (D1).

1 work-hour × $85 per hour = 

$85.

0 85 ........................................... 5,185. 

The FAA estimates the following 

costs to do any necessary actions that 

would be required based on the results 

of the proposed inspections. The agency 

has no way of determining the number 

of airplanes that might need these 

actions. The corresponding letter and 

number in parenthesis refer to the 

specific paragraph in GippsAero SB– 

GA8–2005–23, Issue 8. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Inspecting/replacing forward cargo door slide (A1, 

Steps 2 through 4), corrective action for (A2).

0.50 work-hour × $85 per hour = $42.50 ..................... $175 $217.50 

Reworking cargo door pivot (B2) and reworking/replacing door operating rod assembly (B3).2 work-hours × $85 per hour = $170 ........................... 630 800 

Replacing door handle/handle bush (C) ...................... 1 work-hour × $85 per hour = $85 ............................... 267 352 

Replacing cargo door center rail/slide-center and 

backing plate (D1) and reworking cargo door center 

rail and backing plate (D2).

2 work-hours × $85 per hour = $170 ........................... 152 322 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some of the 

costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

operators. 

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. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA 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 that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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: 

■ a. Removing Airworthiness Directive 

2010–18–06, Amendment 39–16419 (75 

FR 52253, August 25, 2010); and 

■ b. Adding the following new 

airworthiness directive: 

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

2024–0035; Project Identifier MCAI–2023– 

00986–A. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by March 8, 

2024. 

(b) Affected ADs 

This AD replaces AD 2010–18–06, 

Amendment 39–16419 (75 FR 52253, August 

25, 2010). 

(c) Applicability 

This AD applies to GA 8 Airvan (Pty) Ltd 

Model GA8 and GA8–TC320 airplanes, all 

serial numbers, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5230, Cargo/Baggage Doors. 

(e) Unsafe Condition 

This AD was prompted by reports of inflight cargo door separation. The FAA is 

issuing this AD to detect and correct 

excessive wear in the forward cargo door 

slide, which could result in an in-flight 

separation of the cargo door, with possible 

loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Do the applicable actions specified in 

Table 1 to paragraph (g) of this AD at the 

times in Table 1 to paragraph (g) of this AD, 

in accordance with the Accomplishment 

Instructions of GippsAero Service Bulletin 

SB–GA8–2005–23, Issue 8, dated October 11, 

2023 (GippsAero SB–GA8–2005–23, Issue 8). 


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TABLE 1 TO PARAGRAPH (g) 

Paragraphs in accomplishment instructions of 

GippsAero SB–GA8–2005–23, Issue 8 Action Compliance time 

12.1, A1, steps 1 and 2, for backing plate inspection, except where Figure 1 in step 1 

specifies to remove and discard the vertical 

bolt, remove the vertical bolt from service.

Steps 3 through 7, if a backing plate is not installed.

Inspect for the existence of a backing plate on 

the forward slide of the cargo door. If a 

backing plate is not installed, install a backing plate on the forward slide of the cargo 

door, measure the groove width of the forward slide, and replace the slide if it exceeds 0.145 inch at any point or is cracked 

or worn beyond limits.

Inspect within 50 hours time-in-service (TIS) 

or 2 months after the effective date of this 

AD, whichever occurs first. Install, measure, 

and replace before further flight after the inspection. 

12.2, A2, steps 1 and 2 for the inspection ........

12.2, A2, step 3 or 4, and 12.1, A1, steps 2 

through 4, for the follow-on inspection and 

replacement.

Inspect for wear of the forward slide of the 

cargo door by inserting a slide gauge or 

feeler gauge to measure the clearance between the forward slide and the cargo door 

track. If a gap is found, measure the groove 

width of the forward slide and replace the 

slide if the groove width exceeds 0.145 inch 

at any point or is cracked or worn beyond 

limits.

Inspect for wear within 100 hours TIS or 2 

months after the effective date of this AD, 

whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS or 12 

months, whichever occurs first after the 

most recent inspection. Measure the groove 

width and replace the slide before further 

flight after each inspection as necessary. 

12.3, B1, steps 1 through 6 for the inspections 

12.3, B1, steps 2, 3i, and 3ii; 12.4, B2, steps 1 

through 5; and 12.5, B3, steps 1 through 12 

for the corrective actions.

Inspect the cargo door mechanism for contact 

between the operating rod and cargo door 

handle pivot post, inspect the threaded 

studs and rod ends at both ends of the operating rod for bending, and inspect the 

cargo door handle engagement with the 

catch. Perform all applicable corrective actions.

Inspect within 50 hours TIS or 2 months after 

the effective date of this AD, whichever occurs first and thereafter at intervals not to 

exceed 100 hours TIS or 12 months, whichever occurs first after the most recent inspection. Perform all applicable corrective 

actions before further flight. 

12.6, C, steps 1 through 6 ................................. Inspect the cargo door handle to determine if 

an integrated stop is installed and if an integrated stop is not installed, install a cargo 

door handle with an integrated stop. Inspect 

the cargo door handle for beyond normal 

play and replace the handle bush if the 

door handle has beyond normal play.

Within 150 hours TIS or 4 months after the effective date of this AD, whichever occurs 

first. Perform the installation and replacement, as necessary, before further flight 

after the inspection. 

12.7, D1, steps 1 through 10 for the center rail 

cargo door inspection and installation.

12.8, D2, steps 1 through 2, for any necessary 

follow-on rework.

Inspect the center rail of the cargo door to determine if a center rail aft stop is installed 

and if a center rail aft stop is not installed, 

install an aft stop before further flight.

Within 50 hours TIS or 2 months after the effective date of this AD, whichever occurs 

first. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, International Validation 

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 International Validation 

Branch, mail it to the address identified in 

paragraph (i)(2) of this AD or email to: 9- 

AVS-AIR-730-AMOC@faa.gov. If mailing 

information, also submit information by 

email. 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. 

(i) Additional Information 

(1) Refer to Civil Aviation Safety Authority 

(CASA) Australia AD AD/GA8/3 amdt 3, 

dated August 18, 2023, for related 

information. This CASA Australia AD may be 

found in the AD docket at regulations.gov 

under Docket No. FAA–2024–0035. 

(2) For more information about this AD, 

contact Doug Rudolph, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (816) 329– 

4059; email: doug.rudolph@faa.gov. 

(j) 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– 

2005–23, Issue 8, dated October 11, 2023. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact GA8 Airvan (Pty) Ltd, PO 

Box 881, Morwell, Victoria 3840, Australia; 

phone: +61 03 5172 1200; website: 

gippsaero.com.au; email: TECHPUBS@

gippsaero.com.au. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on January 12, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–01018 Filed 1–22–24; 8:45 am] 

BILLING CODE 4910–13–P 


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