78226 Federal Register / Vol. 89, No. 186 / Wednesday, September 25, 2024 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–0223; Project 

Identifier MCAI–2023–00996–T; Amendment 

39–22821; AD 2024–16–15] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A330–200, A330– 

200 freighter, A330–800, and A330–900 

series airplanes; Model A330–301, –302, 

–303, –323, –342, and –343 airplanes; 

and Model A340–312 and –313 

airplanes. This AD was prompted by 

reports of quality non-conformity on 

main landing gear (MLG) axles where 

the high velocity oxygen-fuel (HVOF) 

coating on the bearing journal runout 

areas had a coating that was thicker than 

allowable limits. This AD requires 

repetitive inspections of the affected 

parts (MLG axles) for any discrepancy, 

corrective actions, and eventual 

replacement of affected parts, and 

prohibits the installation of affected 

parts, 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 October 30, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 30, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–0223; 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 

AD, contact EASA, Konrad-AdenauerUfer 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 at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Airworthiness Products Section, 

Operational Safety 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 in the AD docket at 

regulations.gov under Docket No. FAA– 

2024–0223. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 206–231–3229; email 

vladimir.ulyanov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus SAS Model A330– 

200, A330–200 freighter, A330–800, and 

A330–900 series airplanes; Model 

A330–301, –302, –303, –323, –342, and 

–343 airplanes; and Model A340–312 

and –313 airplanes. The NPRM 

published in the Federal Register on 

February 12, 2024 (89 FR 9795). The 

NPRM was prompted by EASA AD 

2023–0167, dated August 30, 2023 

(EASA AD 2023–0167) (also referred to 

as the MCAI), issued by EASA, which 

is the Technical Agent for the Member 

States of the European Union. The 

MCAI states there are reports of quality 

non-conformity on MLG axles where the 

HVOF coating on the bearing journal 

runout areas had a coating thicker than 

allowable limits. This over-thickness 

could lead to damage, cracking, or 

spalling of the protective coating, which 

could expose the base material and 

allow corrosion to develop. This 

condition, if not detected and corrected, 

could lead to a MLG axle failure, 

possibly resulting in a MLG collapse, 

with consequent damage to the airplane 

and injury to occupants. 

In the NPRM, the FAA proposed to 

require repetitive inspections of the 

affected parts (MLG axles) for any 

discrepancy, corrective actions, and 

eventual replacement of affected parts, 

and to prohibit the installation of 

affected parts, as specified in EASA AD 

2023–0167. 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–2024–0223. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

two commenters, Air Line Pilots 

Association, International (ALPA), and 

an anonymous commenter, who 

supported the NPRM without change. 

The FAA received additional 

comments from Delta Air Lines. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request for an Exception To Clarify ReInstallation of an Affected Part 

Delta Air Lines (Delta) requested 

adding an exception to paragraph (h) of 

the proposed AD to clarify note 2 of 

EASA AD 2023–0167 regarding 

installation versus re-installation of 

affected parts. Delta requested that the 

exception state that if an assembly, 

including the bogie beam assembly, 

containing an affected part is removed 

and re-installed during a single 

maintenance visit, that action is not 

considered an installation as specified 

in paragraph (7) of EASA AD 2023– 

0167. Delta stated that note 2 of EASA 

AD 2023–0167 allows the MLG to be 

removed and re-installed during the 

same maintenance visit but does not 

address sub-assemblies containing 

affected parts. 

The FAA agrees to add an exception 

to paragraph (h) of this AD to address 

reinstallation of assemblies, including 

bogie beam assemblies. As defined in 

EASA AD 2023–0167, the affected parts 

are MLG axles with certain part 

numbers and serial numbers. The MLG 

axle is installed in the MLG bogie beam 

assembly. Bogie beam assemblies with 

an affected axle may be removed and 

reinstalled on the MLG as a separate 

unit. Paragraph (7) of EASA AD 2023– 

0167 prohibits the installation of a MLG 

having an affected axle. Note 2 of EASA 

AD 2023–0167 allows removal of MLG 

having an affected axle and subsequent 

reinstallation of that MLG on the same 

airplane, accomplished during a single 

maintenance visit, which is not 

considered as an installation as 

specified in paragraph (7) of EASA AD 

2023–0167. Since the bogie beam 

assembly, with an affected axle, may be 

removed and reinstalled on the MLG as 

a separate unit during a single 

maintenance visit, such reinstallation 

should also not be considered an 

installation as specified in paragraph (7) 

of EASA AD 2023–0167. Paragraph 

(h)(5) has been added to this AD 

accordingly. 


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Federal Register / Vol. 89, No. 186 / Wednesday, September 25, 2024 / Rules and Regulations 78227 

Request for an Exception To Address 

Service Information Error 

Delta requested an exception be 

added to paragraph (h) of the proposed 

AD to address an error in the service 

information referenced in EASA AD 

2023–0167. Delta stated that a 

‘‘Required for Compliance’’ (RC) step, 

paragraph 3.C.(1)(b)1a (in Task set 

A330–A–32–XX–3305–01000–93BA–A), 

specifies to ‘‘remove the cover 

protection of the affected axle,’’ but 

pointed out that a note advises against 

the removal of paint or zinc nickel to 

complete the inspection. Delta added 

that it asked Airbus for clarification and 

that Airbus confirmed that the paint or 

zinc nickel on the HVOF should not be 

removed, and that the step ‘‘remove the 

cover protection of the affected axle’’ 

should be deleted from the service 

information. Delta asserted that adding 

the exception to delete the step would 

eliminate the need to request an 

alternative method of compliance 

(AMOC) when the final AD is 

published. 

The FAA agrees to add an exception 

to paragraph (h) of this AD to address 

the specified error in the procedures for 

a detailed inspection of the affected 

axle. The exception in paragraph (h)(6) 

of this AD has been added for the 

reasons described by Delta. 

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, and any other 

changes described previously, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Material Incorporated by Reference 

Under 1 CFR Part 51 

EASA AD 2023–0167 specifies, for 

certain airplanes, procedures for 

repetitive inspections of the affected 

parts (MLG axles) for any discrepancy 

(damage, cracking, or spalling of HVOF 

coating, or corrosion), doing corrective 

actions including obtaining and 

following repair instructions and 

replacement of affected parts. EASA AD 

2023–0167 also prohibits the 

installation of affected parts, and 

installation of MLG having an affected 

part installed. 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 7 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 

Part and serial number inspection.0.5 work-hours × $85 per 

hour = $42.50 per airplane.

$0 $42.50 .................................... $298. 

Inspection of affected axle ..... Up to 16 work-hours × $85 

per hour = $1,360 per axle, 

per inspection cycle.

0 Up to $1,360 per axle, per inspection cycle.Up to $9,520 per axle, per inspection cycle. 

The FAA estimates the following 

costs to do any necessary on-condition 

actions that would be required based on 

the results of any required actions. The 

FAA has no way of determining the 

number of aircraft that might need these 

on-condition actions: 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Action Labor cost Parts cost Cost per 

product 

Repair ............................................................................ Up to 16 work-hours × $85 per hour = $1,360 ............. $0 $1,360. 

Axle replacement ........................................................... Up to 88 work-hours × $85 per hour = $7,480 ............. 47,126 $54,606. 

Optional replacement of MLG ....................................... Up to 48 work-hours × $85 per hour = $4,080 ............. (*) Up to $4,080. 

* The FAA has received no definitive data on which to base the cost estimates for a replacement MLG. The parts cost must be obtained 

through SAFRAN. 

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 


ddrumheller on DSK120RN23PROD with RULES1
78228 Federal Register / Vol. 89, No. 186 / Wednesday, September 25, 2024 / Rules and Regulations 

(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. 

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 adding 

the following new airworthiness 

directive: 

2024–16–15 Airbus SAS: Amendment 39– 

22821; Docket No. FAA–2024–0223; 

Project Identifier MCAI–2023–00996–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective October 30, 2024. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus airplanes 

identified in paragraphs (c)(1) through (4) of 

this AD, certificated in any category. 

(1) Model A330–201, –202, –203, –223, and 

–243 airplanes. 

(2) Model A330–223F and –243F airplanes. 

(3) Model A330–301, –302, –303, –323, 

–342, –343, –841, and –941 airplanes. 

(4) Model A340–312 and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Unsafe Condition 

This AD was prompted by reports of 

quality non-conformity on main landing gear 

(MLG) axles where the high velocity oxygen 

fuel (HVOF) coating on the bearing journal 

runout areas had excessive coating compared 

to the drawing limits. The FAA is issuing this 

AD to address damage, cracking, or spalling 

of the protective HVOF coating and exposure 

of the base material, which could allow 

corrosion to develop. The unsafe condition, 

if not addressed, could result in a MLG axle 

failure, possibly resulting in a MLG collapse, 

with consequent damage to the airplane and 

injury to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

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 2023– 

0167, dated August 30, 2023 (EASA AD 

2023–0167). 

(h) Exceptions to EASA AD 2023–0167 

(1) Where EASA AD 2023–0167 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) Where paragraph (1) of EASA AD 2023– 

0167 specifies to inspect within 24 months 

after the part entry into service, this AD 

requires inspecting within 30 months after 

the part entry into service or 30 days after the 

effective date of this AD, whichever occurs 

later. 

(3) Paragraph (3) of EASA AD 2023–0167 

specifies ‘‘If, during any inspection as 

required by paragraph (1) of this AD, any 

discrepancy, as defined in the SB, is 

detected, before next flight, contact SAFRAN 

Landing Systems for approved corrective 

action instructions and, within the 

compliance time specified therein, 

accomplish those instructions accordingly. If 

no compliance time is identified in those 

instructions, accomplish the applicable 

corrective action(s) before next flight.’’ This 

AD, however, requires replacing that text 

with ‘‘If, during any inspection as required 

by paragraph (1) of this AD, any discrepancy, 

as defined in the SB, is detected, the 

discrepancy must be repaired before further 

flight using a method approved by the 

Manager, International Validation Branch, 

FAA; or EASA; Airbus SAS’s EASA Design 

Organization Approval (DOA); or SAFRAN 

Landing Systems’ DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature.’’ 

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

section of EASA AD 2023–0167. 

(5) This AD requires replacing the text of 

Note 2 of EASA AD 2023–0167 with 

‘‘Removal of an MLG or an assembly, 

including the bogie beam assembly, having 

an affected part installed from an aeroplane 

and subsequent reinstallation of that MLG or 

assembly, including the bogie beam 

assembly, on the same aeroplane, 

accomplished during a single maintenance 

visit, is not considered as installation as 

specified in paragraph (7) of this EASA AD.’’ 

(6) Where the service information 

referenced in EASA AD 2023–0167 specifies 

to ‘‘remove the cover protection of the 

affected axle’’ prior to inspecting the affected 

part, this AD does not include that 

requirement. 

(i) No Reporting Requirement 

Although the service information 

referenced in EASA AD 2023–0167 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 manager of the International Validation 

Branch, mail it to the address 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; Airbus SAS’s EASA 

Design Organization Approval (DOA); or 

SAFRAN Landing System’s EASA 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)(6), (i), 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 Vladimir Ulyanov, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 206– 

231–3229; email vladimir.ulyanov@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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2023–0167, dated August 30, 

2023. 

(ii) [Reserved] 

(3) For EASA AD 2023–0167, 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 at ad.easa.europa.eu. 

(4) You may view this material at the FAA, 

Airworthiness Products Section, Operational 

Safety Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 


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Federal Register / Vol. 89, No. 186 / Wednesday, September 25, 2024 / Rules and Regulations 78229 

(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 August 6, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–21797 Filed 9–24–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1304; Project 

Identifier MCAI–2023–01134–T; Amendment 

39–22822; AD 2024–16–16] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2020–25– 

07, which applied to certain Embraer 

S.A. Model EMB–550 and EMB–545 

airplanes. AD 2020–25–07 required 

repetitive inspections of the flight deck 

side windows for any cracking or 

delamination, corrective action if 

necessary, and eventual replacement of 

the windows. Since the FAA issued AD 

2020–25–07, additional part numbers 

were added to the installation 

prohibition list. This AD continues to 

require the actions in AD 2020–25–07, 

expands the list of affected parts, and 

prohibits the installation of affected 

parts, as specified in an Ageˆncia 

Nacional de Aviac ̧a ̃o Civil (ANAC) 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 October 30, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 30, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1304; 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 ANAC material identified in 

this AD, contact National Civil Aviation 

Agency (ANAC), Aeronautical Products 

Certification Branch (GGCP), Rua Dr. 

Orlando Feirabend Filho, 230—Centro 

Empresarial Aquarius—Torre B— 

Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́

dos Campos—SP, Brazil; telephone 55 

(12) 3203–6600; email pac@anac.gov.br; 

website anac.gov.br/en/. You may find 

this material on the ANAC website 

sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. 

• 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 at regulations.gov 

under Docket No. FAA–2024–1304. 

FOR FURTHER INFORMATION CONTACT: 

Hassan Ibrahim, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 206–231–3653; email 

Hassan.M.Ibrahim@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–25–07, 

Amendment 39–21349 (85 FR 81385, 

December 16, 2020) (AD 2020–25–07). 

AD 2020–25–07 applied to certain 

Embraer S.A. Model EMB–550 and 

EMB–545 airplanes. AD 2020–25–07 

required repetitive inspections of the 

flight deck side windows for any 

cracking or delamination, corrective 

action if necessary, and eventual 

replacement of the windows. The FAA 

issued AD 2020–25–07 to address cracks 

and delamination, which could cause 

the flight deck side windows to fail and 

lead to an in-flight depressurization 

event. 

The NPRM published in the Federal 

Register on May 17, 2024 (89 FR 43336). 

The NPRM was prompted by AD 2020– 

04–01R02, effective November 2, 2023, 

issued by ANAC, which is the aviation 

authority for Brazil (ANAC AD 2020– 

04–01R02) (also referred to as the 

MCAI). The MCAI states that part 

number (P/N) NP–200402–7 and P/N 

NP–200402–8, made mandatory by the 

previous revisions of the MCAI, have 

not had the expected effect on the fleet 

as premature cracks in the outer layer of 

windows with P/N NP–200402–7 and P/ 

N NP–200402–8 have been found. These 

cracks may be undetected, and the inner 

layer may be subjected to unpredicted 

loads for several flights, which could 

result in window failure and subsequent 

in-flight depressurization events. 

In the NPRM, the FAA proposed to 

continue to require the actions in AD 

2020–25–07, expand the list of affected 

parts, and prohibit the installation of 

affected parts, as specified in ANAC AD 

2020–04–01R02. 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–2024–1304. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the NPRM or on the determination of 

the cost to the public. 

Additional Changes Made to This AD 

The FAA revised paragraph (h)(5) of 

this AD to clarify that the 50 flight cycle 

grace period is ‘‘within 50 flight cycles 

after the effective date of this AD.’’ In 

the proposed AD, the FAA inadvertently 

omitted the wording ‘‘after the effective 

date of this AD.’’ 

After the FAA issued the proposed 

AD, ANAC issued an Errata to ANAC 

AD 2020–04–01R02, effective November 

2, 2023, to clarify the actions if an 

inspection is done and delamination or 

other damage which does not impact the 

ability to properly perform the 

inspection is found. As originally 

written, operators could have concluded 

a windshield needed to be replaced 

even if the only inspection finding was 

delamination in an area that did not 

impede the inspection. The FAA has 

revised paragraph (h)(3) of this AD to 

clarify the action for this condition. 

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 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, and any other changes 

described previously, this AD is 


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