This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

87655 

Vol. 88, No. 242 

Tuesday, December 19, 2023 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 21 

[Docket No. FAA–2022–1378] 

Airworthiness Criteria: Primary 

Category Airworthiness Design Criteria 

for the ICON Aircraft Inc., Model A5–B 

Airplane; Correction 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Issuance of final airworthiness 

criteria; correction. 

SUMMARY: The FAA published a 

document in the Federal Register on 

November 28, 2023, announcing the 

primary category airworthiness design 

criteria for type certification of the ICON 

Aircraft Inc., (ICON) Model A5–B 

airplane. The document contained 

incorrect references to the aircraft and 

engine model numbers. 

DATES: This correction is effective on 

December 19, 2023. 

FOR FURTHER INFORMATION CONTACT: Mr. 

Raymond N. Johnston, Avionics 

Navigation & Flight Deck Unit (AIR– 

626B), Avionics & Electrical Systems 

Section, Technical Policy Branch, 

Policy & Standards Division, Aircraft 

Certification Service, Federal Aviation 

Administration, 901 Locust Street, 

Room 301, Kansas City, MO 64106; 

phone (816) 329–4159, fax (816) 329– 

4090, email raymond.johnston@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On November 20, 2023, the FAA 

issued final airworthiness criteria for 

the ICON Model A5–B airplane, which 

published in the Federal Register on 

November 28, 2023 (88 FR 83019). As 

published, the document incorrectly 

referred to the wrong aircraft and engine 

model numbers. Additionally, the FAA 

has certified the engine, as indicated by 

type certificate data sheet (TCDS) 

E00051EN, and therefore the additional 

airworthiness criteria listed in Table 8: 

FAA Validation of EASA State of Design 

Reciprocating Aircraft Engines is no 

longer required. The criteria as 

published would have applied to an 

engine certified by the European 

Aviation Safety Agency (EASA) that did 

not have a corresponding FAA type 

certificate. 

Correction 

In the Federal Register of Tuesday, 

November 28, 2023, appearing at 88 FR 

83019, make the following corrections: 

1. On page 83019— 

a. In the first column in the 

document’s subject heading, correct 

aircraft model number to read ‘‘A5–B’’; 

b. In the first column, in the SUMMARY

section, correct aircraft model number 

to read ‘‘A5–B’’; 

c. In the first and second columns, 

under the heading ‘‘Background,’’ in the 

second paragraph, correct the engine 

model number ‘‘Rotax 912 iS Sport’’ to 

read ‘‘Rotax 912 iSc2 Sport’’ and correct 

the last sentence of the second 

paragraph to read ‘‘The FAA does not 

plan to issue a TC for the propeller’’; 

d. In the third column, under the 

heading ‘‘Airworthiness Criteria,’’ 

correct the second paragraph to read 

‘‘The airworthiness criteria for the 

issuance of a TC for the ICON Aircraft, 

Inc., Model A5–B airplane, a primary 

category airplane, and its powerplant 

installation is listed in Tables 1 through 

7 below’’; 

2. On page 83020, in ‘‘Table 1: 

Airplane Certification Basis,’’ in the 

subject entry for ‘‘Engine’’— 

a. In the ‘‘Consensus standard or 

regulation’’ column, correct ‘‘14 CFR 

part 33, Amendment 33–34’’ to read ‘‘14 

CFR part 33’’; 

b. In the ‘‘Title and description’’ 

column, correct the description to read 

‘‘Utilize the certification basis as 

indicated for the engine TCDS 

E00051EN’’; and 

3. On page 83022, in the first 

column— 

a. Remove the first paragraph; 

c. Remove ‘‘Table 8: FAA Validation 

of EASA State of Design Reciprocating 

Aircraft Engines’’; and 

b. Remove footnote 2 ‘‘CS–E, 

Amendment 6—Aircraft cybersecurity’’. 

Issued in Washington, District of 

Columbia, on December 14, 2023. 

Min Zhang, 

Acting Manager, Certification Coordination 

Section, Policy and Standards Division, 

Aircraft Certification Service. 

[FR Doc. 2023–27835 Filed 12–18–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1645; Project 

Identifier MCAI–2022–01296–T; Amendment 

39–22613; AD 2023–23–11] 

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) 2019–12– 

07, which applied to all Airbus SAS 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2019–12–07 required replacement of 

both main landing gear (MLG) shock 

absorbers, an identification of affected 

MLG sliding tubes; inspection of 

affected chromium plates and sliding 

tube axles for damage; and replacement 

of the sliding tube if necessary. AD 

2019–12–07 also required repetitive 

inspections of affected MLG sliding 

tubes for cracking, replacement of 

cracked MLG sliding tubes, and 

eventual replacement of each affected 

MLG sliding tube. This AD continues to 

require the actions specified in AD 

2019–12–07 and requires repetitive 

inspections of additional MLG sliding 

tubes, replacement if necessary, and 

eventual replacement of the additional 

MLG sliding tubes. This AD also 

extends the repetitive inspection 

interval. This AD also prohibits the 

installation of affected parts under 

certain conditions. This AD was 

prompted by the FAA’s determination 

that additional MLG sliding tubes are 

affected by the unsafe condition and 


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that the repetitive inspection interval 

may be extended. The FAA is issuing 

this AD to address the unsafe condition 

on these products. 

DATES: This AD is effective January 23, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 23, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 1, 2019 (84 FR 

30579, June 27, 2019). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 22, 2017 (82 FR 

5362, January 18, 2017). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 29, 2007 (72 FR 

29241, May 25, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 23, 2004 (69 FR 

31867, June 8, 2004). 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1645; 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 Airbus service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EIAS, Rond-Point Emile Dewoitine No: 

2, 31700 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; website airbus.com. 

• For Safran and Messier-Dowty 

service information identified in this 

final rule, contact Safran Landing 

Systems, One Carbon Way, Walton, KY 

41094; telephone 859–525–8583; fax 

859–485–8827; website www.safranlanding-systems.com. 

• You may view this service 

information 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 at 

regulations.gov under Docket No. FAA– 

2023–1645. 

FOR FURTHER INFORMATION CONTACT: 

Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; phone: 

206–231–3667; email: 

Timothy.P.Dowling@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–12–07, 

Amendment 39–19662 (84 FR 30579, 

June 27, 2019) (AD 2019–12–07). AD 

2019–12–07 applied to all Airbus SAS 

Model A318–111, –112, –121, and –122 

airplanes; Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 

airplanes; Model A320–211, –212, –214, 

–216, –231, –232, and –233 airplanes; 

and Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

AD 2019–12–07 required replacement of 

both MLG shock absorbers, an 

identification of the part number and 

serial number of the MLG sliding tubes, 

inspection of affected chromium plates 

and sliding tube axles for damage, and 

replacement of the sliding tube if 

necessary. AD 2019–12–07 also required 

repetitive inspections of affected MLG 

sliding tubes for cracking, replacement 

of cracked MLG sliding tubes, and 

eventual replacement of each affected 

MLG sliding tube. The FAA issued AD 

2019–12–07 to address cracking in an 

MLG sliding tube, which could lead to 

failure of an MLG sliding tube resulting 

in MLG collapse, damage to the 

airplane, and injury to passengers. 

The NPRM published in the Federal 

Register on August 1, 2023 (88 FR 

50067). The NPRM was prompted by 

AD 2022–0204R1, dated February 15, 

2023; corrected February 17, 2023, 

issued by The European Union Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Union (EASA AD 2022– 

0204R1) (also referred to as the MCAI). 

The MCAI states that since EASA AD 

2018–0135, dated June 26, 2018, was 

issued (which corresponds to FAA AD 

2019–12–07), two additional cases have 

been reported of cracking at the same 

location of MLG sliding tubes not 

affected by the inspection requirements 

and that service information was issued 

to include additional actions for the 

newly affected MLG sliding tubes. In 

addition, further investigation 

determined the repetitive inspection 

interval may be extended from 5,000 

flight cycles to 10,000 flight cycles. 

In the NPRM, the FAA proposed to 

continue to require the actions specified 

in AD 2019–12–07 and proposed to 

require repetitive inspections of 

additional MLG sliding tubes, 

replacement if necessary, and eventual 

replacement of the additional MLG 

sliding tubes. In the NPRM, the FAA 

also proposed to extend the repetitive 

inspection interval and to prohibit the 

installation of affected parts under 

certain conditions. 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–2023–1645. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

four commenters, including American 

Airlines, SIAEC, United Airlines 

(United), and Delta Air Lines (Delta). 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Allow Parts Inspected Using 

Component Maintenance Manuals 

(CMMs) 

American Airlines, SIAEC, United, 

and Delta requested that the proposed 

AD be revised to identify MLG sliding 

tubes that were inspected using certain 

CMMs identified in EASA AD 2022– 

0204R1 as acceptable parts. American 

Airlines requested that paragraph (w)(1) 

of the proposed AD be revised to 

include CMM references that include 

inspections as acceptable actions for the 

on-wing inspections. Delta requested 

that both paragraph (n)(2) and (w)(1) of 

the proposed AD be revised to include 

parts that have passed inspection using 

the CMMs. American Airlines and 

SIAEC stated that paragraph (w)(1) of 

the proposed AD does not include as 

serviceable parts MLG sliding tubes that 

have been inspected and repaired using 

the CMMs specified in EASA AD 2022– 

0204R1. 

United requested the FAA definition 

of serviceable parts be revised to 

include those that were overhauled per 

the CMMs identified in EASA AD 2022– 

0204R1 and the Safran service 

information identified in EASA AD 

2022–0204R1. 

The FAA agrees to revise paragraphs 

(n)(2) and (w)(1) of this AD, which 

include definitions of affected parts 

with exceptions. This change addresses 

United’s request to revise the definition 

of serviceable parts specified in 

paragraph (w)(2) of this AD. The FAA 

has revised the exception language in 


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paragraphs (n)(2) and (w)(1) of this AD 

to include parts that have passed an 

inspection specified in Safran CMM task 

32–11–33 (K0654), Revision 71, dated 

September 2020, or later; CMM task 32– 

12–25 (K0654), Revision 61, dated 

March 2020, or later; CMM task 32–12– 

12 (K0654), Revision 57, dated 

September 2020, or later; or CMM task 

32–12–22 (K0654), Revision 56, dated 

March 2020, or later; as applicable. 

Regarding the comment that the repair 

of MLG sliding tubes using the CMMs 

specified in EASA AD 2022–0204R1 

was not included in paragraph (w)(1) of 

the proposed AD, with the change to 

paragraph (w)(1) of this AD described 

previously, those repairs are included. 

As specified in paragraph (w)(1) of this 

AD repairs must have been done using 

instructions approved by the Manager, 

International Section, Transport 

Standards Branch, FAA; or EASA; or 

Airbus SAS’s EASA DOA. If approved 

by the DOA, the approval must include 

the DOA-authorized signature. 

Request for Revise Format 

United requested that the FAA revise 

the format of the proposed AD. United 

stated that the proposed AD restates the 

requirements of previously issued FAA 

ADs under paragraph (g) through (v) of 

the proposed AD and adds new 

requirements from paragraph (w) 

through (cc) of the proposed AD. United 

stated it found the restatements to be 

unnecessary and that the proposed AD 

could be simplified and made easier to 

read. United recommended requiring 

operators to comply with the 

requirements of Airbus Service Bulletin 

A320–32–1441, Revision 2, dated 

August 23, 2022, with the noted 

exceptions of the compliance time. 

The FAA acknowledges that this is a 

complex AD; however, the FAA 

disagrees with the request. In most 

supersedures where there are retained 

requirements, the FAA structures the 

AD by including the retained ‘‘old’’ 

requirements in ‘‘Restatement’’ 

paragraphs and the ‘‘new’’ requirements 

in the ‘‘New’’ paragraphs of the AD. 

This allows operators that already 

accomplished the ‘‘old’’ requirements of 

an existing AD to show compliance with 

the corresponding retained 

requirements in the new AD without 

having to show compliance with two 

ADs. The FAA has not revised this AD 

in this regard. 

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. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Service 

Bulletin A320–32–1441, Revision 02, 

dated August 23, 2022. This service 

information specifies procedures for 

inspections of the MLG sliding tubes for 

cracking and corrective actions (which 

includes replacing the MLG sliding 

tubes). 

The FAA also reviewed Safran 

Service Bulletin 200–32–321, Revision 

4, dated November 3, 2021; and Safran 

Service Bulletin 201–32–68, Revision 4, 

dated November 3, 2021. These 

documents specify the part numbers 

and serial numbers of the affected MLG 

sliding tubes. These documents are 

distinct since they apply to different 

airplane models. 

This AD also requires the following 

service information, which the Director 

of the Federal Register approved for 

incorporation by reference as of August 

1, 2019 (84 FR 30579, June 27, 2019). 

• Airbus Service Bulletin A320–32– 

1441, Revision 01, dated December 14, 

2017. 

• Messier-Dowty Service Bulletin 

200–32–286, Revision 3, dated October 

3, 2008. 

• Messier-Dowty Service Bulletin 

201–32–43, Revision 3, dated October 3, 

2008. 

• Safran Service Bulletin 200–32– 

321, Revision 2, dated October 3, 2017. 

• Safran Service Bulletin 201–32–68, 

Revision 2, dated October 3, 2017. 

This AD also requires Airbus Service 

Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014, 

which the Director of the Federal 

Register approved for incorporation by 

reference as of February 22, 2017 (82 FR 

5362, January 18, 2017). 

This AD also requires Airbus Service 

Bulletin A320–32A1273, Revision 02, 

including Appendix 01, dated May 26, 

2005, which the Director of the Federal 

Register approved for incorporation by 

reference as of June 29, 2007 (72 FR 

29241, May 25, 2007). 

This AD also requires Airbus All 

Operators Telex A320–32A1273, 

Revision 01, dated May 6, 2004, which 

the Director of the Federal Register 

approved for incorporation by reference 

as of June 23, 2004 (69 FR 31867, June 

8, 2004). 

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 

The FAA estimates that this AD 

affects 1,525 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 paragraph (g) 

of AD 2019–12–07 (297 airplanes *).

8 work-hours × $85 per hour = 

$680.

Up to $45,310 .... Up to $45,990 .... Up to $13,659,030.* 

Retained actions from paragraphs 

(h) and (j) of AD 2019–12–07.

18 work-hours × $85 per hour = 

$1,530.

$0 ....................... $1,530 ................ $2,333,250. 

Retained actions from paragraphs 

(o), (p), and (q) of AD 2019–12– 

07.

13 work-hours × $85 per hour = 

$1,105.

Up to $3,920 ...... Up to $5,025 ...... Up to $7,663,125. 


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ESTIMATED COSTS FOR REQUIRED ACTIONS—Continued 

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

New actions (in paragraphs (o), (p), 

and (q) of this AD).

9 work-hours × $85 per hour = 

$765.

Up to $3,920 ...... Up to $4,685 ...... Up to $7,144,625. 

* Operators should note that, although all U.S.-registered airplanes are subject to the retained requirements of paragraph (g) of this AD, there 

are only 297 possible affected MLG sliding tubes in the worldwide fleet. The FAA has no way of knowing how many affected MLG sliding tubes, 

if any, are installed in U.S.-registered airplanes. 

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

Labor cost Parts cost Cost per 

product 

7 work-hours × $85 per hour = $595 ...................................................................................................................... $1,960 $2,555 

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 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. 

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 

(AD) 2019–12–07, Amendment 39– 

19662 (84 FR 30579, June 27, 2019); and 

■ b. Adding the following new AD: 

2023–23–11 Airbus SAS: Amendment 39– 

22613; Docket No. FAA–2023–1645; 

Project Identifier MCAI–2022–01296–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 23, 2024. 

(b) Affected ADs 

This AD replaces AD 2019–12–07, 

Amendment 39–19662 (84 FR 30579, June 

27, 2019) (AD 2019–12–07). 

(c) Applicability 

This AD applies to Airbus SAS airplanes 

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

this AD, certificated in any category, all 

manufacturer serial numbers (MSNs). 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing gear. 

(e) Reason 

This AD was prompted by a determination 

that cracks were found in the main landing 

gear (MLG) sliding tubes due to certain 

manufacturing defects that might not be 

identified using the current on-wing 

scheduled inspections. In addition, since AD 

2019–12–07 was issued, the FAA has 

determined that additional MLG sliding 

tubes are affected by the unsafe condition. 

The FAA is issuing this AD to address 

cracking in an MLG sliding tube, which 

could lead to failure of an MLG sliding tube 

resulting in MLG collapse, damage to the 

airplane, and injury to passengers. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Replacement, With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2019–12–07, with no 

changes. Within 41 months after June 29, 

2007 (the effective date of AD 2007–11–11, 

Amendment 39–15068 (72 FR 29241, May 25, 

2007) (AD 2007–11–11)), replace all MLG 

shock absorbers equipped with MLG sliding 

tubes having serial numbers listed in Airbus 

All Operators Telex (AOT) A320–32A1273, 

Revision 01, dated May 6, 2004; or the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32A1273, Revision 02, 

including Appendix 01, dated May 26, 2005; 

with new or serviceable MLG shock 

absorbers equipped with MLG sliding tubes 

having serial numbers not listed in Airbus 

AOT A320–32A1273, Revision 01, dated May 

6, 2004; or the Accomplishment Instructions 

of Airbus Service Bulletin A320–32A1273, 

Revision 02, including Appendix 01, dated 

May-26, 2005; using a method approved by 

the Manager, International Section, Transport 


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Standards Branch, FAA; or the European 

Aviation Safety Agency (EASA); or Airbus 

SAS’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

As of June 29, 2007, only Airbus Service 

Bulletin A320–32A1273, Revision 02, 

including Appendix 01, dated May 26, 2005, 

may be used to determine the affected MLG 

sliding tubes. 

Note 1 to paragraph (g): Guidance on the 

replacement specified in paragraph (g) of this 

AD can be found in Airbus A318/A319/ 

A320/A321 Aircraft Maintenance Manual 

Chapter 32–11–13, page block 401. 

(h) Retained MLG Sliding Tube Part Number 

and Serial Number Identification, With No 

Changes 

This paragraph restates the requirements of 

paragraph (h) of AD 2019–12–07, with no 

changes. Within three months after February 

22, 2017 (the effective date of AD 2017–01– 

11, Amendment 39–18778 (82 FR 5362, 

January 18, 2017) (AD 2017–01–11)): Do an 

inspection to identify the part number and 

serial number of the MLG sliding tubes 

installed on the airplane. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number and 

serial number of the MLG sliding tubes can 

be conclusively determined from that review. 

(i) Retained Identification of Airplanes, With 

an Updated Reference 

This paragraph restates the requirements of 

paragraph (i) of AD 2019–12–07, with an 

updated reference. An airplane with an MSN 

not listed in figure 1 to paragraph (i) of this 

AD is not affected by the requirements of 

paragraph (j) of this AD, provided it can be 

determined that no MLG sliding tube having 

a part number and serial number listed in 

figure 2 to paragraph (i) of this AD has been 

installed on that airplane since first flight of 

the airplane. 


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Figure 1 to Paragraph (i) -Affected Airplanes Listed by MSN 

Affected Airplanes Listed by MSN 

0179 0214 0296 0412 0558 0604 

0607 0668 0704 0720 0726 0731 

0754 0771 0799 0828 0841 0855 

0909 0914 0925 0939 0986 1028 

1030 1041 1070 1083 1093 1098 

1108 1148 1294 1356 2713 2831 
87660 Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 


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Figure 2 to Paragraph (i) -Affected MLG Sliding Tubes 

Part Number Serial Number 

201160302 78B 

201160302 1016Bl 1 

201160302 1144B 

201371302 B4493 

201371302 B4513 

201371302 SS4359 

201371302 B4530 

201371302 B4517 

201371302 B4568 

201371302 B4498 

201371302 4490B 

201371302 B202-4598 

201371302 B165-4623 

201371302 B244-4766 

201371302 B267-4794 

201371302 B272-4813 

201160302 1108B 

201371304 B041-4871 

201371304 B045-4869 

201371304 B00l-4781 

201371304 B0Sl-4892 

201371304 Bl 10-1952 

201371304 B054-4891 

201371304 B063-4921 

201371304 B071-4911 

201371304 B071-4917 

201371304 B0S0-1933 

201371304 B117-5010 

201371304 B120-4989 

201371304 B132-2023 

201371304 B114-1956 

201371304 B208-2009 
Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 87661 

(j) Retained Inspections, With an Updated 

Reference 

This paragraph restates the inspections 

required by paragraph (j) of AD 2019–12–07, 

with an updated reference. For each MLG 

sliding tube identified as required by 

paragraph (h) of this AD, having a part 

number and serial number listed in figure 2 

to paragraph (i) of this AD: Within 3 months 

after February 22, 2017 (the effective date of 

AD 2017–01–11) inspect affected MLG axles 

and brake flanges by doing a detailed visual 

inspection of the chromium plates for 

damage, and a Barkhausen noise inspection 

of the MLG sliding tube axles for damage, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. For Model A318 series 

airplanes, use the procedures specified for 

Model A319 series airplanes in Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014. 


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Part Number Serial Number 

201371304 B133-1947 

201371304 Bl54-5037 

201371304 B89 4952 

201371304 B129-1964 

201371304 B227-2010 

201371304 Bl 70-5031 

201371304 B182-5047 

201371304 B239-2053 

201371304 B1401-2856 

201371304 B1813-3142 

201371304 Bl 16-5004 

201522353 B0l 1-149 

201522350 B014-25 

201522350 B019-56 

201522350 B019-57 

201522350 B021-69 

201522350 B022-60 

201522353 B03-ll 1 

201522353 B03-110 

201522353 Bl12-317 

201522353 Bl 74-351 

201522353 Bl 79-392 

201383350 4377B 

201383350 4393B 

201383350 B1831 

201383350 B1832 

201383350 SS4355B 

201383350 SS4400B 
87662 Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 

(k) Retained Corrective Action for Paragraph 

(j) of This AD, With No Changes 

This paragraph restates the requirements of 

paragraph (k) of 2019–12–07, with no 

changes. If, during any inspection required 

by paragraph (j) of this AD, any damage is 

detected: Before further flight, replace the 

MLG sliding tube with a serviceable MLG 

sliding tube, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1416, including 

Appendix 01, dated March 10, 2014. For 

Model A318 series airplanes, use the 

procedures specified for Model A319 series 

airplanes in Airbus Service Bulletin A320– 

32–1416, including Appendix 01, dated 

March 10, 2014. 

(l) Retained Definition for Serviceable MLG 

Sliding Tube, With Updated References 

This paragraph restates the definition for 

serviceable MLG sliding tube specified in 

paragraph (l) of AD 2019–12–07, with 

updated references. For the purpose of 

paragraph (k) of this AD, a serviceable MLG 

sliding tube is defined as an MLG sliding 

tube that meets the criterion in either 

paragraph (l)(1) or (2) of this AD. 

(1) An MLG sliding tube having a part 

number and serial number not listed in figure 

2 to paragraph (i) of this AD. 

(2) An MLG sliding tube having a part 

number and serial number listed in figure 2 

to paragraph (i) of this AD that has passed 

the inspections required by paragraph (j) of 

this AD. 

(m) Retained Parts Installation Prohibition, 

With Updated References 

This paragraph restates the parts 

installation prohibition specified in 

paragraph (m) of AD 2019–12–07, with 

updated references. 

(1) For airplanes that have an MLG sliding 

tube installed that has a part number and 

serial number listed in figure 2 to paragraph 

(i) of this AD: After an airplane is returned 

to service following accomplishment of the 

actions required by paragraphs (h), (i), and (j) 

of this AD, no person may install on any 

airplane an MLG sliding tube having a part 

number and serial number listed in figure 2 

to paragraph (i) of this AD, unless that MLG 

sliding tube has passed the inspection 

required by paragraph (j) of this AD. 

(2) For airplanes that, as of February 22, 

2017 (the effective date of AD 2017–01–11), 

do not have an MLG sliding tube installed 

that has a part number and serial number 

listed in figure 2 to paragraph (i) of this AD: 

No person may install, on any airplane, an 

MLG sliding tube having a part number and 

serial number listed in figure 2 to paragraph 

(i) of this AD unless that MLG sliding tube 

has passed the inspection required by 

paragraph (j) of this AD. 

(n) Retained Definitions, With New 

Exception in Paragraph (n)(2) of This AD 

This paragraph restates the definitions 

specified in paragraph (n) of AD 2019–12–07, 

with new exception in paragraph (n)(2) of 

this AD. For the purpose of paragraphs (o), 

(p), (q), (r), and (s) of this AD, the following 

definitions apply. 

(1) Affected MLG shock absorber: An MLG 

shock absorber having a part number and 

serial number as identified in Messier-Dowty 

Service Bulletin 200–32–286, Revision 3, 

dated October 3, 2008, for Model A318, 

A319, and A320 series airplanes; and 

Messier-Dowty Service Bulletin 201–32–43, 

Revision 3, dated October 3, 2008, for Model 

A321 series airplanes. 

(2) Affected MLG sliding tube: An MLG 

sliding tube having a part number and serial 

number as identified in Appendix B of Safran 

Service Bulletin 200–32–321, Revision 2, 

dated October 3, 2017, for Model A318, 

A319, and A320 series airplanes, or Safran 

Service Bulletin 201–32–68, Revision 2, 

dated October 3, 2017, for Model A321 series 

airplanes; except parts identified in 

paragraphs (n)(2)(i) and (ii) of this AD and 

those parts that, after the inspection specified 

(n)(2)(i) or (ii) of this AD, have been repaired, 

using instructions approved by the Manager, 

International Section, Transport Standards 

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

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

Note 2 to the introductory text of 

paragraph (n)(2) of this AD: The affected 

MLG sliding tubes identified in paragraph 

(n)(2) of this AD are referred to as affected 

‘‘Batch 1’’ MLG sliding tubes in EASA AD 

2022–0204R1, dated February 15, 2023; 

corrected February 17, 2023. 

(i) Parts that passed an inspection as 

specified in Safran Service Bulletin 200–32– 

321 or Safran Service Bulletin 201–32–68, as 

applicable. 

(ii) Parts that have passed an inspection as 

specified in Safran component maintenance 

manual (CMM) task 32–11–33 (K0654), 

Revision 71, dated September 2020, or later; 

CMM task 32–12–25 (K0654), Revision 61, 

dated March 2020, or later; CMM task 32–12– 

12 (K0654), Revision 57, dated September 

2020, or later; or CMM task 32–12–22 

(K0654), Revision 56, dated March 2020, or 

later; as applicable. 

(3) Serviceable MLG sliding tube: An MLG 

sliding tube that is not affected, or an affected 

MLG sliding tube, that has not exceeded 

10,000 flight cycles since first installation on 

an airplane, or an affected MLG sliding tube 

that, within the last 5,000 flight cycles before 

installation on an airplane, passed an 

inspection specified in Airbus Service 

Bulletin A320–32–1441. 

(o) Retained Repetitive Inspections, With 

New Service Information and Extended 

Inspection Interval 

This paragraph restates the repetitive 

inspections required by paragraph (o) of AD 

2019–12–07, with new service information 

and extended inspection interval. At the 

compliance time specified in figure 3 to 

paragraph (o) of this AD, and thereafter at 

intervals not to exceed 10,000 flight cycles: 

Do a detailed inspection of each affected 

MLG sliding tube, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1441, Revision 01, 

dated December 14, 2017; or Airbus Service 

Bulletin A320–32–1441, Revision 02, dated 

August 23, 2022. As of the effective date of 

this AD, only use Airbus Service Bulletin 

A320–32–1441, Revision 02, dated August 

23, 2022, for the actions required by this 

paragraph. 

Note 3 to paragraph (o): If no reliable data 

regarding the number of flight cycles 

accumulated by the MLG sliding tube are 

available, operators may refer to the guidance 

specified in Chapter 5.2, ‘‘Traceability,’’ of 

Section 1, of Part 1 of the Airbus A318/A319/ 

A320/A321 Airworthiness Limitations 

Section. 

(p) Retained Corrective Actions for Certain 

Inspections Required by Paragraph (o) of 

This AD, With New Service Information 

This paragraph restates the corrective 

actions required by paragraph (p) of AD 


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Figure 3 to Paragraph ( o) - Initial Compliance Time for MLG Sliding Tube Inspection 

Initial Compliance Time for MLG Sliding Tube Inspection 

(whichever occurs later, AB, or C) 

A Prior to exceeding 10,000 flight cycles since first installation of an affected 

MLG sliding tube on an airplane. 

B Before exceeding 10,000 flight cycles since last MLG sliding tube overhaul. 

C Within 5,000 flight cycles or 25 months, whichever occurs first after 

August 1, 2019 (the effective date of AD 2019-12-07). 
Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 87663 

2019–12–07 for certain inspections required 

by paragraph (o) of this AD, with new service 

information. For airplanes on which any 

inspection required by paragraph (o) of this 

AD has been done before the effective date 

of this AD, comply with paragraph (p)(1) or 

(2) of this AD, as applicable. For airplanes on 

which any inspection required by paragraph 

(o) of this AD has been done on or after the 

effective date of this AD, comply with 

paragraph (y)(1) or (3) of this AD, as 

applicable. 

(1) If any crack is detected on an MLG 

sliding tube, before further flight, replace that 

MLG sliding tube with a serviceable MLG 

sliding tube, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1441, Revision 01, 

dated December 14, 2017; or Airbus Service 

Bulletin A320–32–1441, Revision 02, dated 

August 23, 2022. 

(2) Replacement of an MLG on an airplane 

with an MLG having a serviceable MLG 

sliding tube installed is an acceptable 

method to comply with the requirements of 

paragraph (p)(1) of this AD for that airplane. 

(q) Retained Part Replacement, With New 

Reference to New Parts Installation 

Limitation 

This paragraph restates the parts 

replacement required by paragraph (q) of AD 

2019–12–07, with new reference to new parts 

installation limitation. 

(1) Within 10 years after August 1, 2019 

(the effective date of AD 2019–12–07), 

replace each affected MLG sliding tube with 

an MLG sliding tube that is not affected. 

Installation of an MLG sliding tube that is not 

affected on an airplane constitutes 

terminating action for the repetitive 

inspections required by paragraph (o) of this 

AD for that airplane. As of the effective date 

of this AD, operators also must comply with 

the parts installation limitation specified in 

paragraph (aa) of this AD. 

(2) Replacement of an MLG on an airplane 

with an MLG that does not have an affected 

MLG sliding tube installed is an acceptable 

method to comply with the requirements of 

paragraph (q)(1) of this AD for that airplane. 

As of the effective date of this AD, operators 

also must comply with the parts installation 

limitation specified in paragraph (aa) of this 

AD. 

(r) Retained Parts Installation Limitation, 

With a New Exception to Paragraph (r)(1) of 

This AD 

This paragraph restates the parts 

installation limitation specified in paragraph 

(r) of AD 2019–12–07, with a new exception 

to paragraph (r)(1) of this AD. 

(1) As of August 1, 2019 (the effective date 

of AD 2019–12–07) and before the effective 

date of this AD, no person may install on any 

airplane an affected MLG shock absorber 

assembly containing a discrepant MLG 

sliding tube part number. As of the effective 

date of this AD, comply with the parts 

installation limitation specified in paragraph 

(aa)(1) of this AD. 

(2) Do not install an affected MLG sliding 

tube on any airplane as specified in 

paragraph (r)(2)(i) or (ii) of this AD, as 

applicable. 

(i) For an airplane with an affected MLG 

sliding tube installed as of August 1, 2019 

(the effective date of AD 2019–12–07): After 

replacement of each affected MLG sliding 

tube as required by paragraph (q) of this AD. 

(ii) For an airplane that does not have an 

affected MLG sliding tube installed as of 

August 1, 2019 (the effective date of AD 

2019–12–07): As of August 1, 2019. 

(s) Retained Identification of Airplanes Not 

Affected by Certain Requirements of This 

AD, With No Changes 

This paragraph restates the airplanes not 

affected provision specified in paragraph (s) 

of AD 2019–12–07, with no changes. An 

airplane on which Airbus Modification 

161202 or Modification 161346 has been 

installed in production is not affected by the 

requirements of paragraphs (g), (h), (j), (o), 

and (q) of this AD, provided it has been 

verified that no affected MLG sliding tube is 

installed on that airplane. 

(t) Retained Credit for Previous Actions, 

With No Changes 

This paragraph restates the credit for 

previous actions specified in paragraph (t) of 

AD 2019–12–07, with no changes. 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before June 

29, 2007 (the effective date of AD 2007–11– 

11), using Airbus AOT A320–32A1273, 

Revision 01, dated May 6, 2004. This 

document was incorporated by reference in 

AD 2004–11–13, Amendment 39–13659 (69 

FR 31867, June 8, 2004). 

(2) This paragraph provides credit for the 

initial inspection and applicable corrective 

actions required by paragraphs (o) and (p) of 

this AD if those actions were performed 

before August 1, 2019 (the effective date of 

AD 2019–12–07), using the Accomplishment 

Instructions in Airbus Service Bulletin 

A320–32–1441, dated December 28, 2016. 

(u) Retained Service Information Exception, 

With No Changes 

This paragraph restates the service 

information exception specified in paragraph 

(u) of AD 2019–12–07, with no changes. The 

service information specified in paragraph (g) 

of this AD has instructions to send any 

cracked part to Messier-Dowty. This AD does 

not include such a requirement. 

(v) Retained No Reporting Requirement, 

With New Service Information 

This paragraph restates the no reporting 

requirement provision specified in paragraph 

(v) of AD 2019–12–07, with new service 

information. Although Airbus Service 

Bulletin A320–32–1441, Revision 01, dated 

December 14, 2017; and Airbus Service 

Bulletin A320–32–1441, Revision 02, dated 

August 23, 2022; specify to submit certain 

information to the manufacturer, and specify 

that action as ‘‘RC’’ (required for 

compliance), this AD does not include that 

requirement. 

(w) New Definitions for New Requirements 

of This AD 

For the purpose of paragraphs (x), (y), (z), 

(aa), and (bb) of this AD, the following 

definitions apply. 

(1) Affected MLG sliding tube: An MLG 

sliding tube having a part number identified 

in Safran Service Bulletin 200–32–321, 

Revision 4, dated November 3, 2021, for 

Model A318, A319, and A320 series 

airplanes, or Safran Service Bulletin 201–32– 

68, Revision 4, dated November 3, 2021, for 

Model A321 series airplanes; except those 

having a serial number identified in 

Appendix B of Safran Service Bulletin 200– 

32–321, Revision 2, dated October 3, 2017, 

for Model A318, A319, and A320 series 

airplanes, or Safran Service Bulletin 201–32– 

68, Revision 2, dated October 3, 2017, for 

Model A321 series airplanes; and except 

parts identified in paragraphs (w)(1)(i) and 

(ii) of this AD and those parts that, after the 

inspection specified (w)(1)(i) or (ii) of this 

AD, have been repaired, using instructions 

approved by the Manager, International 

Section, Transport Standards Branch, FAA; 

or EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

Note 4 to the introductory text of 

paragraph (w)(1) of this AD: The affected 

MLG sliding tubes identified in paragraph 

(w)(1) of this AD are referred to as affected 

‘‘Batch 2’’ MLG sliding tubes in EASA AD 

2022–0204R1, dated February 15, 2023; 

corrected February 17, 2023. 

(i) Parts that passed an inspection as 

specified in Safran Service Bulletin 200–32– 

321 or Safran Service Bulletin 201–32–68, as 

applicable 

(ii) Parts that have passed an inspection as 

specified in Safran CMM task 32–11–33 

(K0654), Revision 71, dated September 2020, 

or later; CMM task 32–12–25 (K0654), 

Revision 61, dated March 2020, or later; 

CMM task 32–12–12 (K0654), Revision 57, 

dated September 2020, or later; or CMM task 

32–12–22 (K0654), Revision 56, dated March 

2020, or later; as applicable. 

(2) Serviceable MLG sliding tube: Any 

MLG sliding tube other than those identified 

in paragraphs (w)(2)(i) thru (iii) of this AD. 

(i) Any MLG sliding tube having a part 

number and serial number listed in figure 2 

to paragraph (i) of this AD. 

(ii) Any affected MLG sliding tube 

identified in paragraph (n)(2) of this AD. 

(iii) Any affected MLG sliding tube 

identified in paragraph (w)(1) of this AD. 

(x) New Inspections for Additional Affected 

MLG Sliding Tubes 

At the compliance time specified in figure 

4 to paragraph (x) of this AD, and thereafter 

at intervals not to exceed 10,000 flight cycles: 

Do a detailed inspection of each affected 

MLG sliding tube, as defined in paragraph 

(w)(1) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–32–1441, Revision 02, 

dated August 23, 2022. 


lotter on DSK11XQN23PROD with RULES1
87664 Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 

Note 5 to paragraph (x): If no reliable data 

regarding the number of flight cycles 

accumulated by the MLG sliding tube are 

available, operators may refer to the guidance 

specified in Chapter 5.2, ‘‘Traceability,’’ of 

Section 1, of Part 1 of the Airbus A318/A319/ 

A320/A321 Airworthiness Limitations 

Section. 

(y) New Corrective Actions 

(1) For airplanes on which any inspection 

required by paragraph (o) of this AD has been 

done on or after the effective date of this AD: 

If any crack is detected on an MLG sliding 

tube, before further flight, replace that MLG 

sliding tube with a serviceable MLG sliding 

tube, as defined in paragraph (w)(2) of this 

AD, in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1441, Revision 02, dated August 23, 2022. 

(2) If, during any inspection required by 

paragraph (x) of this AD, any crack is 

detected on an MLG sliding tube: Before 

further flight, replace that MLG sliding tube 

with a serviceable MLG sliding tube, as 

defined in paragraph (w)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

32–1441, Revision 02, dated August 23, 2022. 

(3) Replacement of an MLG on an airplane 

with an MLG having a serviceable MLG 

sliding tube, as defined in paragraph (w)(2) 

of this AD, installed is an acceptable method 

to comply with the requirements of 

paragraph (y)(1) or (2) of this AD for that 

airplane. 

(z) New Replacement for Additional Affected 

Parts 

(1) Within 10 years after the effective date 

of this AD, replace each affected MLG sliding 

tube, as defined in paragraph (w)(1) of this 

AD, with a serviceable MLG sliding tube, as 

defined in paragraph (w)(2) of this AD. 

Replacement on an airplane of all affected 

MLG sliding tubes with serviceable MLG 

sliding tubes constitutes terminating action 

for the repetitive inspections required by 

paragraph (x) of this AD for that airplane. 

(2) Replacement of an MLG on an airplane 

with an MLG that has a serviceable MLG 

sliding tube, as defined in paragraph (w)(2) 

of this AD, installed is an acceptable method 

to comply with the requirement of paragraph 

(z)(1) of this AD for that airplane. 

(aa) New Parts Installation Limitation 

(1) As of the effective date of this AD, no 

person may install on any airplane an MLG 

shock absorber assembly that contains any 

MLG sliding tube identified in paragraphs 

(aa)(i) through (iii) of this AD. 

(i) Any MLG sliding tube having a part 

number and serial number listed in figure 2 

to paragraph (i) of this AD. 

(ii) Any affected MLG sliding tube 

identified in paragraph (n)(2) of this AD. 

(iii) Any affected MLG sliding tube 

identified in paragraph (w)(1) of this AD. 

(2) Do not install an affected MLG sliding 

tube identified in paragraph (w)(1) of this AD 

on any airplane as specified in paragraph 

(aa)(2)(i) or (ii) of this AD, as applicable. 

(i) For an airplane with an affected MLG 

sliding tube installed as of the effective date 

of this AD: After replacement of each affected 

MLG sliding tube as required by paragraph 

(z) of this AD. 

(ii) For an airplane that does not have an 

affected MLG sliding tube installed as of the 

effective date of this AD: As of the effective 

date of this AD. 

(bb) New Identification of Airplanes Not 

Affected by Certain Requirements of This AD 

An airplane on which Airbus Modification 

161202 or Modification 161346 has been 

installed in production is not affected by the 

requirements for affected MLG sliding tubes 

in paragraph (x) of this AD and the 

requirement of paragraph (z) of this AD, 

provided it has been verified that no affected 

MLG sliding tube, as defined in paragraph 

(w)(2) of this AD, is installed on that 

airplane. 

(cc) No Reporting Requirement for New 

Actions 

Although Airbus Service Bulletin A320– 

32–1441, Revision 01, dated December 14, 

2017; and Airbus Service Bulletin A320–32– 

1441, Revision 02, dated August 23, 2022; 

specify to submit certain information to the 

manufacturer, and specify that action as 

‘‘RC’’ (required for compliance), this AD does 

not include that requirement. 

(dd) Additional AD Provisions 

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

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

information, also submit information by 

email. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) AMOCs approved for AD 2019–12–07 

are approved as AMOCs for the 

corresponding provisions of this AD. 

(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 the European Union 

Aviation Safety Agency (EASA); or Airbus 

SAS’s EASA DOA. If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraphs (u), (v), and (dd)(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. 

(ee) Additional Information 

(1) Refer to EASA AD 2022–0204R1, dated 

February 15, 2023; corrected February 17, 

2023; for related information. This EASA AD 

may be found in the AD docket at 

regulations.gov under Docket No. FAA– 

2023–1645. 

(2) For more information about this AD, 

contact Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: 206–231– 

3667; email: Timothy.P.Dowling@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (ff)(8) and (10) of this AD. 


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Figure 4 to Paragraph (x) - Initial Compliance Time for MLG Sliding Tube Inspection 

Initial Compliance Time for MLG Sliding Tube Inspection 

(whichever occurs later, AB, or C) 

A Prior to exceeding 10,000 flight cycles since first installation of an affected 

MLG sliding tube on an airplane. 

B Before exceeding 10,000 flight cycles since last MLG sliding tube overhaul. 

C For affected MLG sliding tubes: Within 2,000 flight cycles after the effective 

date of this AD. 
Federal Register / Vol. 88, No. 242 / Tuesday, December 19, 2023 / Rules and Regulations 87665 

(ff) 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. 

(3) The following service information was 

approved for IBR on January 23, 2024. 

(i) Airbus Service Bulletin A320–32–1441, 

Revision 02, dated August 23, 2022. 

(ii) Safran Service Bulletin 200–32–321, 

Revision 4, dated November 3, 2021. 

(iii) Safran Service Bulletin 201–32–68, 

Revision 4, dated November 3, 2021. 

(4) The following service information was 

approved for IBR on August 1, 2019 (84 FR 

30579, June 27, 2019). 

(i) Airbus Service Bulletin A320–32–1441, 

Revision 01, dated December 14, 2017. 

(ii) Messier-Dowty Service Bulletin 200– 

32–286, Revision 3, dated October 3, 2008. 

(iii) Messier-Dowty Service Bulletin 201– 

32–43, Revision 3, dated October 3, 2008. 

(iv) Safran Service Bulletin 200–32–321, 

Revision 2, dated October 3, 2017. 

(v) Safran Service Bulletin 201–32–68, 

Revision 2, dated October 3, 2017. 

(5) The following service information was 

approved for IBR on February 22, 2017 (82 

FR 5362, January 18, 2017). 

(i) Airbus Service Bulletin A320–32–1416, 

including Appendix 01, dated March 10, 

2014. 

(ii) [Reserved] 

(6) The following service information was 

approved for IBR on June 29, 2007 (72 FR 

29241, May 25, 2007). 

(i) Airbus Service Bulletin A320–32A1273, 

Revision 02, including Appendix 01, dated 

May 26, 2005. 

(ii) [Reserved] 

(7) The following service information was 

approved for IBR on June 23, 2004 (69 FR 

31867, June 8, 2004). 

(i) Airbus All Operators Telex A320– 

32A1273, Revision 01, dated May 6, 2004. 

(ii) [Reserved] 

(8) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EIAS, Rond-Point 

Emile Dewoitine No: 2, 31700 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airworth-eas@

airbus.com; website airbus.com. 

(9) For Safran and Messier-Dowty service 

information identified in this AD, contact 

Safran Landing Systems, One Carbon Way, 

Walton, KY 41094; telephone (859) 525– 

8583; fax (859) 485–8827; internet 

www.safran-landing-systems.com. 

(10) You may view this service information 

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. 

(11) 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 November 16, 2023. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2023–27681 Filed 12–18–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 97 

[Docket No. 31521; Amdt. No. 4091] 

Standard Instrument Approach 

Procedures, and Takeoff Minimums 

and Obstacle Departure Procedures; 

Miscellaneous Amendments 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This rule establishes, amends, 

suspends, or removes Standard 

Instrument Approach Procedures 

(SIAPS) and associated Takeoff 

Minimums and Obstacle Departure 

procedures (ODPs) for operations at 

certain airports. These regulatory 

actions are needed because of the 

adoption of new or revised criteria, or 

because of changes occurring in the 

National Airspace System, such as the 

commissioning of new navigational 

facilities, adding new obstacles, or 

changing air traffic requirements. These 

changes are designed to provide safe 

and efficient use of the navigable 

airspace and to promote safe flight 

operations under instrument flight rules 

at the affected airports. 

DATES: This rule is effective December 

19, 2023. The compliance date for each 

SIAP, associated Takeoff Minimums, 

and ODP is specified in the amendatory 

provisions. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of December 

19, 2023. 

ADDRESSES: Availability of matters 

incorporated by reference in the 

amendment is as follows: 

For Examination 

1. U.S. Department of Transportation, 

Docket Ops–M30, 1200 New Jersey 

Avenue SE, West Bldg., Ground Floor, 

Washington, DC 20590–0001. 

2. The FAA Air Traffic Organization 

Service Area in which the affected 

airport is located; 

3. The office of Aeronautical 

Information Services, 6500 South 

MacArthur Blvd., Oklahoma City, OK 

73169 or, 

4. 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. 

Availability 

All SIAPs and Takeoff Minimums and 

ODPs are available online free of charge. 

Visit the National Flight Data Center at 

nfdc.faa.gov to register. Additionally, 

individual SIAP and Takeoff Minimums 

and ODP copies may be obtained from 

the FAA Air Traffic Organization 

Service Area in which the affected 

airport is located. 

FOR FURTHER INFORMATION CONTACT: 

Thomas J. Nichols, Flight Procedures 

and Airspace Group, Flight 

Technologies and Procedures Division, 

Flight Standards Service, Federal 

Aviation Administration. Mailing 

Address: FAA Mike Monroney 

Aeronautical Center, Flight Procedures 

and Airspace Group, 6500 South 

MacArthur Blvd., STB Annex, Bldg. 26, 

Room 217, Oklahoma City, OK 73099. 

Telephone (405) 954–1139. 

SUPPLEMENTARY INFORMATION: This rule 

amends 14 CFR part 97 by establishing, 

amending, suspending, or removes 

SIAPS, Takeoff Minimums and/or 

ODPS. The complete regulatory 

description of each SIAP and its 

associated Takeoff Minimums or ODP 

for an identified airport is listed on FAA 

form documents which are incorporated 

by reference in this amendment under 5 

U.S.C. 552(a), 1 CFR part 51, and 14 

CFR 97.20. The applicable FAA Forms 

8260–3, 8260–4, 8260–5, 8260–15A, 

8260–15B, when required by an entry 

on 8260–15A, and 8260–15C. 

The large number of SIAPs, Takeoff 

Minimums and ODPs, their complex 

nature, and the need for a special format 

make publication in the Federal 

Register expensive and impractical. 

Further, pilots do not use the regulatory 

text of the SIAPs, Takeoff Minimums or 

ODPs, but instead refer to their graphic 

depiction on charts printed by 

publishers or aeronautical materials. 

Thus, the advantages of incorporation 

by reference are realized and 

publication of the complete description 

of each SIAP, Takeoff Minimums and 

ODP listed on FAA form documents is 

unnecessary. This amendment provides 

the affected CFR sections and specifies 

the types of SIAPS, Takeoff Minimums 

and ODPs with their applicable effective 

dates. This amendment also identifies 


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