11720 Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

Model EC225LP helicopters, serial numbers 

2650, 2651, 2653, 2684, 2712, and 2796, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code: 5210, Passenger crew doors. 

(e) Unsafe Condition 

This AD was prompted by a report of 

incorrect door opening instructions on the 

placard located on the right-hand (RH) side 

of the VIP flap door. The FAA is issuing this 

AD to address and correct placards on the RH 

side VIP flap door. The unsafe condition, if 

not addressed, could prevent jettisoning of 

the RH side VIP flap door during an 

emergency situation, possibly obstructing 

evacuation and resulting in injury to 

occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified in paragraphs (h) and 

(i) of this AD: Comply with all required 

actions and compliance times specified in, 

and in accordance with, European Union 

Aviation Safety Agency (EASA) AD 2022– 

0072, dated April 26, 2022 (EASA AD 2022– 

0072). 

(h) Exceptions to EASA AD 2022–0072 

(1) Where EASA AD 2022–0072 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where EASA AD 2022–0072 refers to 

flight hours, this AD requires using hours 

time-in-service. 

(3) Where the paragraph defined as placard 

installation in EASA AD 2022–0072 states 

‘‘in accordance with the instructions of the 

ASB,’’ for this AD, replace that text with ‘‘in 

accordance with the Accomplishment 

Instructions, paragraph 3.B of the ASB.’’ 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2022–0072 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) 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 § 39.19. In accordance 

with § 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, send it to 

the attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-AVS-AIR-730-AMOC@faa.gov. 

(1) 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. 

(k) Related Information 

For more information about this AD, 

contact William McCully, Aviation Safety 

Engineer, FAA, International Validation 

Branch, FAA, 1600 Stewart Ave., Suite 410, 

Westbury, NY 11590; phone (404) 474–5548; 

email william.mccully@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) European Union Aviation Safety Agency 

(EASA) AD 2022–0072, dated April 26, 2022. 

(ii) [Reserved] 

(3) For EASA AD 2022–0072, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

easa.europa.eu. You may find the EASA 

material on the EASA website at 

ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 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 24, 2024. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–03137 Filed 2–14–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2136; Project 

Identifier MCAI–2023–00759–T; Amendment 

39–22659; AD 2024–01–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–16– 

11, which applied to certain Airbus SAS 

Model A300 F4–605R and FR–622R 

airplanes. AD 2019–16–11 required 

repetitive high frequency eddy current 

(HFEC) inspections of the aft lower deck 

cargo door (LDCD) frame forks; a onetime check of the LDCD clearances; a 

one-time detailed visual inspection of 

hooks, eccentric bushes, and x-stops; 

and corrective actions if necessary. This 

AD was prompted by a determination 

that the threshold for the (repetitive) 

HFEC inspection needs to be corrected, 

and the LDCD frame forks modified. 

This AD continues to require the actions 

in AD 2019–16–11, requires correcting 

the HFEC inspection threshold and 

modifying the LDCD frame forks, and 

prohibits the installation of affected 

LDCDs under certain conditions; as 

specified in a European Union Aviation 

Safety Agency (EASA) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective March 21, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 21, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–2136; 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 final rule, the mandatory 

continuing airworthiness information 

(MCAI), any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

Material Incorporated by Reference: 

• For EASA material identified in this 

final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne, 

Germany; telephone +49 221 8999 000; 

email ADs@easa.europa.eu; website 

easa.europa.eu. You may find this 

material on the EASA website 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 

216th Street, Des Moines, WA. For 

information on the availability of this 

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

It is also available in the AD docket at 

regulations.gov under Docket No. FAA– 

2023–2136. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aviation Safety Engineer, FAA, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone 206– 

231–3225; email dan.rodina@faa.gov. 

SUPPLEMENTARY INFORMATION: 


khammond on DSKJM1Z7X2PROD with RULES
Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations 11721 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–16–11, 

Amendment 39–19714 (84 FR 45061, 

August 28, 2019) (AD 2019–16–11). AD 

2019–16–11 applied to certain Airbus 

SAS Model A300 F4–605R and F4–622R 

airplanes. AD 2019–16–11 required 

repetitive HFEC inspections of the aft 

LDCD frame forks; a one-time check of 

the LDCD clearances; a one-time 

detailed visual inspection of hooks, 

eccentric bushes, and x-stops; and 

corrective actions if necessary. The FAA 

issued AD 2019–16–11 to address 

cracked or ruptured aft LDCD frames, 

which could allow loads to be 

transferred to the remaining structural 

elements. This condition could lead to 

the rupture of one or more vertical aft 

LDCD frames, which could result in 

reduced structural integrity of the aft 

LDCD. 

The NPRM published in the Federal 

Register on October 31, 2023 (88 FR 

74369). The NPRM was prompted by 

AD 2023–0117, dated June 13, 2023, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union (EASA AD 2023–0117) 

(also referred to as the MCAI). The 

MCAI states that based on more detailed 

stress analyses, it has been determined 

that the threshold for the (repetitive) 

HFEC inspection could be extended 

from 12,500 flight hours to 26,455 flight 

hours for those affected parts installed 

on an LDCD that has been modified or 

replaced. It was also determined that an 

incorrect HFEC inspection threshold 

had been defined for the affected parts 

that have not been modified or replaced. 

Additional widespread fatigue damage 

analysis determined that all frame forks 

of affected LDCDs are susceptible to 

crack development, which compromises 

the structural integrity of the LDCD and 

therefore of the airplane. 

In the NPRM, the FAA proposed to 

continue to require the actions in AD 

2019–16–11 and require correcting the 

HFEC inspection threshold, modifying 

the LDCD frame forks, and prohibit the 

installation of affected LDCDs under 

certain conditions, as specified in EASA 

AD 2023–0117. The FAA is issuing this 

AD to address the unsafe condition on 

these products. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–2136. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

FedEx Express and the Air Line Pilots 

Association, International (ALPA), who 

supported the NPRM without change. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is 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 referenced above. The FAA 

reviewed the relevant data, considered 

the comments received, and determined 

that air safety requires adopting this AD 

as proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on this product. Except for 

minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

EASA AD 2023–0117 specifies 

procedures for repetitive HFEC 

inspections for cracks of the aft LDCD 

frame forks; a one-time check of the 

LDCD clearances; a one-time detailed 

visual inspection for signs of wear on 

the hooks, eccentric bushes, and xstops; and corrective actions if 

necessary. In addition, EASA AD 2023– 

0117 specifies procedures for modifying 

frame forks that have not been 

reinforced. EASA AD 2023–0117 also 

prohibits the installation of affected 

LDCDs under certain conditions. 

This material 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 

The FAA estimates that this AD 

affects 58 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

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

operators 

Retained actions from AD 

2019–16–11.

15 work-hours × $85 per hour 

= $1,275.

$0 $1,275 .................................... $73,950. 

New actions ............................ Up to 38 work-hours × $85 

per hour = $3,230.

850 Up to $4,080 .......................... Up to $236,640. 

The FAA has received no definitive 

data on which to base the cost estimates 

for certain on-condition repairs 

specified in this 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. 

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 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) 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. 


khammond on DSKJM1Z7X2PROD with RULES
11722 Federal Register / Vol. 89, No. 32 / Thursday, February 15, 2024 / Rules and Regulations 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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 

■ 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 

2019–16–11, Amendment 39–19714 (84 

FR 45061, August 28, 2019); and 

■ b. Adding the following new 

Airworthiness Directive: 

2024–01–08 Airbus SAS: Amendment 39– 

22659; Docket No. FAA–2023–2136; 

Project Identifier MCAI–2023–00759–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 21, 2024. 

(b) Affected ADs 

This AD replaces AD 2019–16–11, 

Amendment 39–19714 (84 FR 45061, August 

28, 2019) (AD 2019–16–11). 

(c) Applicability 

This AD applies to Airbus SAS Model 

A300 F4–605R and F4–622R airplanes, 

certificated in any category, as identified in 

European Union Aviation Safety Agency 

(EASA) AD 2023–0117, dated June 13, 2023 

(EASA AD 2023–0117). 

(d) Subject 

Air Transport Association (ATA) of 

America Code: 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by a report of two 

adjacent frame forks that were found cracked 

on the aft lower deck cargo door (LDCD) of 

two airplanes during scheduled maintenance, 

and a determination that certain compliance 

times need to be revised. The FAA is also 

issuing this AD to address the susceptibility 

of the frame forks of affected LDCDs to 

develop cracks, which could lead to 

additional rupture of one or more LDCD 

frame forks, compromising the structural 

integrity of the LDCD and therefore of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, EASA AD 2023–0117. 

(h) Exceptions to EASA AD 2023–0117 

(1) Where EASA AD 2023–0117 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where Table 2 of EASA AD 2023–0117 

refers to the effective date of EASA AD 2015– 

0152R1, dated May 23, 2017, this AD 

requires using November 5, 2018 (the 

effective date of AD 2018–20–06, 

Amendment 39–19440 (83 FR 49265, October 

1, 2018)). 

(3) Where Table 2 of EASA AD 2023–0117 

refers to the effective date of EASA AD 2015– 

0152, dated July 24, 2015, this AD requires 

using January 26, 2017 (the effective date of 

AD 2016–25–03, Amendment 39–18729 (81 

FR 93801, December 22, 2016)). 

(4) Where paragraph (6) of EASA AD 2023– 

0117 uses the phrase ‘‘before next flight, 

contact Airbus for approved corrective action 

instructions, and within the compliance time 

specified therein, accomplish those 

instructions accordingly,’’ this AD requires 

replacing those words with ‘‘repair cracking 

before further flight using a method approved 

by the Manager, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature.’’ 

(5) This AD does not adopt the ‘‘Remarks’’ 

section of EASA AD 2023–0117. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2023–0117 specifies 

to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) 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 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the International Validation Branch, send 

it to the attention of the person identified in 

paragraph (k) of this AD. Information may be 

emailed to: 9-AVS-AIR-730-AMOC@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the responsible Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (h)(4) and (j)(2) of 

this AD, if any service information contains 

procedures or tests that are identified as RC, 

those procedures and tests must be done to 

comply with this AD; any procedures or tests 

that are not identified as RC are 

recommended. Those procedures and tests 

that are not identified as RC may be deviated 

from using accepted methods in accordance 

with the operator’s maintenance or 

inspection program without obtaining 

approval of an AMOC, provided the 

procedures and tests identified as RC can be 

done and the airplane can be put back in an 

airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(k) Additional Information 

For more information about this AD, 

contact Dan Rodina, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3225; email dan.rodina@faa.gov. 

(l) 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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0117, dated June 13, 2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0117, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; website 

easa.europa.eu. You may find this EASA AD 

on the EASA website ad.easa.europa.eu. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

Street, Des Moines, WA. For information on 

the availability of this material at the FAA, 

call 206–231–3195. 

(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 9, 2024. 

Caitlin Locke, 

Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2024–03080 Filed 2–14–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2145; Project 

Identifier MCAI–2023–00358–T; Amendment 

39–22660; AD 2024–01–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc., Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


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