81320 Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, AIR–520, Continued Operational 

Safety Branch, FAA, to make those findings. 

To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Luis Cortez-Muniz, Aviation Safety 

Engineer, FAA, 2200 South 216th St., Des 

Moines, WA 98198; phone: 206–231–3958; 

email: luis.a.cortez-muniz@faa.gov. 

(2) Material identified in this AD that is not 

incorporated by reference is available at the 

address specified in paragraph (l)(3) of this 

AD. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the material listed in this paragraph 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

777–53A0100 RB, dated March 16, 2023. 

(ii) Boeing Multi Operator Message MOM– 

MOM–24–0054–01B, dated January 26, 2024. 

(3) For Boeing material, contact Boeing 

Commercial Airplanes, Attention: 

Contractual & Data Services (C&DS), 2600 

Westminster Blvd., MC 110–SK57, Seal 

Beach, CA 90740–5600; telephone 562–797– 

1717; website myboeingfleet.com. 

(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. 

(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 1, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–23117 Filed 10–7–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1886; Project 

Identifier AD–2023–00429–T; Amendment 

39–22841; AD 2024–18–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2009–01– 

02, which applied to certain Boeing 

Model 737–600, –700, –700C, –800, and 

–900 series airplanes. AD 2009–01–02 

required an inspection of frames 

between body station (BS) 360 and BS 

907 to determine if certain support 

brackets of the air conditioning (A/C) 

outlet extrusions are installed, 

inspections for cracking of the frames 

around the attachment holes of the 

subject brackets, and repair if necessary. 

AD 2009–01–02 also requires installing 

new, improved fittings for all support 

brackets of the A/C outlet extrusions 

between BS 360 and BS 907. This AD 

was prompted by numerous reports of 

multiple cracks in the frame around the 

attachment holes of the support bracket 

of the A/C outlet extrusion, and the 

determination that certain repairs might 

develop fatigue cracks that could result 

in the inability of the frame to sustain 

limit load and therefore must be 

inspected. This AD would continue to 

require the actions specified in AD 

2009–01–02 and would also require 

repetitive inspections for cracking of 

certain repairs, and repair if necessary. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective November 

12, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 12, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of February 27, 2009 (74 FR 

4117, January 23, 2009). 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1886; 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, 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 Boeing material identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Contractual & Data 

Services (C&DS), 2600 Westminster 

Blvd., MC 110 SK57, Seal Beach, CA 

90740–5600; telephone 562–797–1717; 

website myboeingfleet.com. 

• 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 at regulations.gov 

under Docket No. FAA–2023–1886. 

FOR FURTHER INFORMATION CONTACT: 

Owen F. Bley-Male, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, 

Des Moines, WA 98198; phone: 206– 

231–3992; email: Owen.F.Bley-Male@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–01–02, 

Amendment 39–15780 (74 FR 4117, 

January 23, 2009) (AD 2009–01–02). AD 

2009–01–02 applied to certain Boeing 

Model 737–600, –700, –700C, –800, and 

–900 series airplanes. The NPRM 

published in the Federal Register on 

September 25, 2023 (88 FR 65637). The 

NPRM was prompted by numerous 

reports of multiple cracks in the frame 

around the attachment holes of the 

support bracket of the A/C outlet 

extrusion and the determination that 

certain repairs might develop fatigue 

cracks that could result in the inability 

of the frame to sustain limit load and 

therefore must be inspected. In the 

NPRM, the FAA proposed to continue to 

require a one-time general visual 

inspection of frames between BS 360 

and BS 907 to determine if certain 

support brackets of the A/C outlet 

extrusions are installed; medium- and 

high-frequency eddy current inspections 

for cracking of the frames around the 

attachment holes of the subject brackets; 

repair if necessary; and installation of 

new, improved fittings for all support 

brackets of the A/C outlet extrusions 

between BS 360 and BS 907. The NPRM 

also proposed to require repetitive 

inspections for cracking of certain 

repairs, and repair if necessary. The 

FAA is issuing this AD to prevent frame 


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cracking, which, if not corrected, could 

lead to a severed frame that, combined 

with cracking of the chemically milled 

steps in the skin above the Stringer 10 

lap splice, could result in rapid 

decompression of the airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from an 

individual who supported the NPRM 

without change. 

The FAA received additional 

comments from Aviation Partners 

Boeing, The Boeing Company (Boeing), 

Southwest Airlines (SWA), United 

Airlines (UAL), and an individual. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Determine Estimated Cost 

An individual commented that the 

NPRM stated that there is no definitive 

data on which to estimate the labor cost 

(for the repairs), so the basis for this 

estimated cost is unclear. The 

commenter suggested an estimate using 

cost data for operations similar to those 

required by this AD, making estimates 

more robust. 

The FAA cannot pre-determine oncondition actions before the inspections 

required by this AD are actually 

completed. The work-hours to complete 

repairs will be unique to each airplane. 

For the other actions required by this 

AD, the FAA used estimated costs that 

were provided by the design approval 

holder. No changes have been made to 

this AD in this regard. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

incorporation of Supplemental Type 

Certificate (STC) ST00830SE for 

installation of blended or split scimitar 

winglets does not affect the 

accomplishment of the manufacturer’s 

service instructions. 

The FAA agrees with the commenter 

that STC ST00830SE does not affect the 

accomplishment of the manufacturer’s 

service instructions. Therefore, the 

installation of STC ST00830SE does not 

affect the ability to accomplish the 

actions required by this AD. The FAA 

has not changed this AD in this regard. 

Request for Correction of the Skin Lap 

Splice Location 

Boeing stated that the NPRM 

incorrectly identified the location of the 

skin lap splice. The NPRM referred to 

‘‘cracking of the skin lap splice above 

stringer 10.’’ Boeing requested that 

language be corrected to ‘‘cracking of 

the chemically milled steps in the skin 

above Stringer 10 lap splice’’ to match 

the language in Boeing Alert Service 

Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022. 

The FAA agrees with the request and 

has revised the ‘‘Background’’ section of 

this final rule and the ‘‘Unsafe 

Condition’’ in paragraph (e) of this AD 

accordingly. 

Request To Add a General Visual 

Inspection for Cracks 

Boeing noted that Boeing Alert 

Service Bulletin 737–25A1544, Revision 

4, dated February 15, 2022, requires a 

general visual inspection (GVI) to detect 

cracks, not just to determine if certain 

support brackets of the A/C outlet 

extrusions are installed at certain 

frames. Boeing requested that a GVI be 

required to also detect cracks. 

The FAA agrees with the request. The 

inspections specified in Part 2 of Boeing 

Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, 

include a GVI to detect cracks. The 

‘‘Material Incorporated by Reference 

under 1 CFR part 51’’ section of this 

final rule and paragraph (g)(2) of this 

AD have been revised to include a GVI 

as an inspection method. 

Request To Revise the Applicability 

Statement 

Boeing stated that paragraph (c), 

‘‘Applicability,’’ of the proposed AD 

incorrectly identified the referenced 

service information as Boeing ‘‘Special 

Attention’’ Service Bulletin 737– 

25A1544, Revision 4, dated February 15, 

2022, and explained that Revision 4 of 

this service information is an ‘‘alert’’ 

service bulletin. The correct reference is 

Boeing Alert Service Bulletin 737– 

25A1544, Revision 4, dated February 15, 

2022. 

The FAA agrees and has revised 

paragraph (c) of this AD accordingly. 

Request To Correct Special Attention 

Service Bulletin 

Boeing stated that a certain Boeing 

special attention service bulletin is 

incorrectly identified under ‘‘Actions 

Since AD 2009–01–02 Was Issued’’ of 

the NPRM. Boeing pointed out that the 

NPRM incorrectly identified the service 

bulletin number as ‘‘737–25A1544.’’ 

The correct service bulletin number is 

‘‘737–25–1544.’’ 

The FAA partially agrees. The FAA 

agrees that the specified service bulletin 

number was stated incorrectly in the 

NPRM. However, since that section of 

the NPRM is not restated in this final 

rule, no change is necessary in this 

regard. 

Request To Revise AMOC Provisions 

SWA stated that paragraph (j) of the 

proposed AD requires inspection of 

repairs installed on the BS 907 frame at 

the compliance times given in Table 2 

of Boeing Alert Service Bulletin 737– 

25A1544, Revision 4, dated February 15, 

2022. SWA mentioned that Table 2 

requires post-repair inspections for 

repairs that were installed per Boeing 

Special Attention Service Bulletin 737– 

25–1544, Revision 3, dated May 16, 

2016; or Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated 

February 15, 2022; and does not address 

repairs that were installed by any other 

means. SWA proposed revising 

paragraph (m)(4) of the proposed AD to 

extend alternative method of 

compliance (AMOC) approval to 

paragraph (j) of the proposed AD, 

provided the AMOC approval contains 

a damage tolerance evaluation. SWA 

believes that individually approved 

repairs that contain an AMOC to AD 

2009–01–02, with a damage tolerance 

analysis as a Category A or Category B 

repair (as defined in Boeing SRM 51– 

00–06), provide an equivalent level of 

safety. 

The FAA disagrees with the request. 

Only repairs installed per Boeing 

Special Attention Service Bulletin 737– 

25–1544, Revision 3, dated May 16, 

2016; or Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated 

February 15, 2022; are subject to the 

requirements of paragraph (j) of this AD. 

Repairs installed by any other means are 

not subject to the requirements of 

paragraph (j) of this AD, so the proposed 

AMOC to paragraph (j) would not be 

applicable. The FAA has not changed 

this AD in this regard. 

Request To Clarify Airplanes Affected 

by New Requirements 

UAL supported the NPRM, and 

requested clarification of the airplanes 

affected by paragraph (j) of the proposed 

AD. UAL stated that some airplanes had 

repairs to the STA 907 frame performed 

before release of Boeing Special 

Attention Service Bulletin 737–25– 

1544, Revision 3, dated May 16, 2016. 

UAL added that these repairs were 

coordinated with Boeing and received 

Form 8100–9 approvals as AMOCs to 

paragraph (g) of AD 2009–01–02 and are 

considered Category B damage tolerance 

repairs that also require additional 

inspections as defined in the 8100–9 

approval. UAL stated that Table 2 of the 

‘‘Compliance’’ paragraph of Boeing 

Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022 (as 

specified in paragraph (j) of the 

proposed AD), applies only to airplanes 


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on which a frame repair has been done 

at STA 907 in accordance with Boeing 

Special Attention Service Bulletin 737– 

25–1544, Revision 3, dated May 16, 

2016; or Boeing Alert Service Bulletin 

737–25–1544, Revision 4, dated 

February 15, 2022. UAL therefore stated 

that Category B repairs via Form 8100– 

9 should be excluded from paragraph (j) 

of the proposed AD. 

The FAA provides the following 

clarification. As stated previously, only 

repairs installed per Boeing Special 

Attention Service Bulletin 737–25– 

1544, Revision 3, dated May 16, 2016; 

or Boeing Alert Service Bulletin 747– 

25A1544, Revision 4, dated February 15, 

2022; are subject to the requirements of 

paragraph (j) of this AD. Repairs 

installed by any other means are not 

subject to the requirements of paragraph 

(j) of this AD. Therefore, no change to 

this AD is necessary. 

Conclusion 

The FAA reviewed the relevant data, 

considered any 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 these 

products. 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 

The FAA reviewed Boeing Alert 

Service Bulletin 737–25A1544, Revision 

4, dated February 15, 2022. This 

material specifies procedures for a onetime general visual inspection of frames 

between BS 360 and BS 907 to 

determine if certain support brackets of 

the A/C outlet extrusions are installed; 

a general visual inspection and low-, 

medium-, and high-frequency eddy 

current inspections for cracking of the 

frames around the attachment holes of 

the subject brackets, and repair if 

necessary; and installation of new, 

improved fittings for all support 

brackets of the A/C outlet extrusions 

between BS 360 and BS 907. This 

material also specifies procedures for 

repetitive detailed and high-frequency 

eddy current inspections for cracking of 

certain repairs at BS 907 and repair if 

necessary. 

This AD also requires Boeing Special 

Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 

2008, which the Director of the Federal 

Register approved for incorporation by 

reference as of February 27, 2009 (74 FR 

4117, January 23, 2009). 

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 ADDRESSES. 

Costs of Compliance 

The FAA estimates that this AD 

affects 738 airplanes of U.S. registry. 

The FAA estimates the following costs 

to comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

General visual inspection (retained actions from AD 2009-01-02).1 work-hour × $85 per hour = $85 ....... $0 ...................... $85 ......................... $62,730. 

Eddy current inspections (retained actions from AD 2009-01-02).Up to 216 work-hours × $85 per hour 

= Up to $18,360.

$0 ...................... Up to $18,360 ........ Up to $13,549,680. 

Replace support fittings (retained actions from AD 2009–01–02).Up to 346 work-hours × $85 per hour 

= Up to $29,410.

Up to $28,789 ... Up to $58,199 ........ Up to $42,950,862. 

Post-repair inspections (new action) .... 42 work-hours × $85 per hour = 

$3,570 per inspection cycle.

$0 ...................... $3,570 per inspection cycle.$2,634,660 per inspection cycle. 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition repairs that would 

be required based on the results of the 

inspections 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. 

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) 2009–01–02, Amendment 39– 

15780 (74 FR 4117, January 23, 2009); 

and 

■ b. Adding the following new AD: 

2024–18–07 The Boeing Company: 

Amendment 39–22841; Docket No. 


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Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations 81323 

FAA–2023–1886; Project Identifier AD– 

2023–00429–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 12, 2024. 

(b) Affected ADs 

This AD replaces AD 2009–01–02, 

Amendment 39–15780 (74 FR 4117, January 

23, 2009) (AD 2009–01–02). 

(c) Applicability 

This AD applies to Boeing Model 737–600, 

–700, –700C, –800, and –900 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishing. 

(e) Unsafe Condition 

This AD was prompted by numerous 

reports of multiple cracks in the frame 

around the attachment holes of the support 

bracket of the air conditioning (A/C) outlet 

extrusion. Also, the FAA determined that 

certain repairs done to comply with AD 

2009–01–02 might develop fatigue cracks 

that could result in the inability of the frame 

to sustain limit load and must be inspected. 

The FAA is issuing this AD to address frame 

cracking, which, if not corrected, could lead 

to a severed frame that, combined with 

cracking of the chemically milled steps in the 

skin above the Stringer 10 lap splice, could 

result in rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection, With New Material 

This paragraph restates the requirements of 

paragraph (f) of AD 2009–01–02, with new 

material. Before the accumulation of 36,000 

total flight cycles, or within 72 months after 

February 27, 2009 (the effective date of AD 

2009–01–02), whichever occurs later, except 

as required by paragraph (i) of this AD: Do 

a general visual inspection to determine if 

the support brackets of the A/C outlet 

extrusions between body station (BS) 360 and 

BS 907 have two-rivet attachment fittings in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 2008, or 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022; except 

at the locations identified in the notes of Step 

3.B.1 of Part 1 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–25–1544, Revision 1, 

dated January 16, 2008, or Boeing Alert 

Service Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022. As of the effective 

date of this AD, only use Boeing Alert 

Service Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022, for the actions 

required by paragraph (g) of this AD. 

(1) For any support bracket attached with 

three or more rivets: No further action is 

required by paragraph (g) of this AD. 

(2) For any subject support bracket having 

a two-rivet attachment fitting: Before the 

accumulation of 36,000 total flight cycles, or 

within 72 months after February 27, 2009 

(the effective date of AD 2009–01–02), 

whichever occurs later, except as required by 

paragraph (i) of this AD, do general visual, 

medium- and high-frequency eddy current 

inspections for cracking of the frame around 

the attachment holes of the support bracket, 

in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 2008, or 

do general visual, low-, medium- and highfrequency eddy current inspections for 

cracking of the frame around the attachment 

holes of the support bracket, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated February 15, 

2022. If any cracking is discovered, before 

further flight, repair the cracking in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 2008, or 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, except 

as required by paragraph (k)(2) of this AD. As 

of the effective date of this AD, only use 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, for the 

actions required by paragraph (g)(2) of this 

AD. 

(h) Retained Modification, With New 

Material 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–01–02, with new 

material. Except as required by paragraph (i) 

of this AD: Before the accumulation of 36,000 

total flight cycles, or within 72 months after 

February 27, 2009 (the effective date of AD 

2009–01–02), whichever occurs later, replace 

the support fittings of all A/C outlet 

extrusions between BS 360 and BS 907 with 

new, improved support fittings, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 2008, or 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022. As of 

the effective date of this AD, only use Boeing 

Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, for the 

actions required by paragraph (h) of this AD. 

(i) Retained Compliance Time for Certain 

Airplanes, With No Changes 

This paragraph restates the compliance 

time specified in paragraph (h) of AD 2009– 

01–02, with no changes. For airplanes on 

which Boeing Business Jet (BBJ) lower cabin 

altitude modification is incorporated in 

accordance with Supplemental Type 

Certificate (STC) ST01697SE (6,500 feet 

maximum cabin altitude in lieu of 8,000 

feet): Before the accumulation of 18,000 total 

flight cycles, or within 72 months after 

February 27, 2009 (the effective date of AD 

2009–01–02), whichever occurs later, do the 

actions specified in paragraphs (g) and (h) of 

this AD. 

(j) New Requirements of This AD 

For Groups 1 through 4 and Group 6 as 

identified in Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated February 15, 

2022: Except as specified in paragraph (k) of 

this AD: At the applicable time specified in 

Table 2 of the ‘‘Compliance’’ paragraph of 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, do a 

detailed inspection and a high-frequency 

eddy current inspection for cracking of the 

repaired area at frame BS 907, and do all 

applicable repairs before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated February 15, 

2022. Repeat the inspections thereafter at the 

applicable time specified in Table 2 of the 

‘‘Compliance’’ paragraph of Boeing Alert 

Service Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022. 

(k) Exceptions to Service Bulletin 

Specifications 

(1) Where the Compliance Time column of 

Table 2 in the ‘‘Compliance’’ paragraph of 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022, uses the 

phrase ‘‘the Revision 4 date of this Service 

Bulletin,’’ this AD requires using ‘‘the 

effective date of this AD.’’ 

(2) Where Boeing Alert Service Bulletin 

737–25A1544, Revision 4, dated February 15, 

2022, specifies contacting Boeing, this AD 

requires repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(3) For airplanes on which BBJ Lower 

Cabin Altitude STC ST01697SE (drs.faa.gov/ 

browse/excelExternalWindow/ 

0812969A86AF879B86257664

00600105.0001) has been incorporated, the 

flight-cycle related compliance times for the 

inspections required by paragraph (j) of this 

AD are different from those specified in 

Table 2 of the ‘‘Compliance’’ paragraph in 

Boeing Alert Service Bulletin 737–25A1544, 

Revision 4, dated February 15, 2022. All 

initial compliance times specified in total 

flight cycles or flight cycles must be reduced 

to half of those specified in Table 2 of the 

‘‘Compliance’’ paragraph in Boeing Alert 

Service Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022. All repetitive 

interval compliance times specified in flight 

cycles must be reduced to one-quarter of 

those specified in Table 2 of the 

‘‘Compliance’’ paragraph in Boeing Alert 

Service Bulletin 737–25A1544, Revision 4, 

dated February 15, 2022. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraphs (g) and (h) of 

this AD, if those actions were performed 

before February 27, 2009 (the effective date 

of AD 2009–01–02), using Boeing Special 

Attention Service Bulletin 737–25–1544, 

dated October 4, 2006. 

(2) This paragraph provides credit for the 

actions specified in paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Special Attention Service Bulletin 

737–25–1544, Revision 2, dated March 23, 


ddrumheller on DSK120RN23PROD with RULES1
81324 Federal Register / Vol. 89, No. 195 / Tuesday, October 8, 2024 / Rules and Regulations 

2011; or Boeing Special Attention Service 

Bulletin 737–25–1544, Revision 3, dated May 

16, 2016. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, AIR–520, Continued 

Operational Safety 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 AIR–520, Continued 

Operational Safety Branch, send it to the 

attention of the person identified in 

paragraph (n)(1) of this AD. Information may 

be emailed to: AMOC@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by The Boeing Company 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, AIR–520, Continued Operational 

Safety Branch, FAA, to make those findings. 

To be approved, the repair method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(4) AMOCs approved for AD 2009–01–02 

are approved as AMOCs for the 

corresponding provisions of this AD. 

(n) Related Information 

(1) For more information about this AD, 

contact Owen F. Bley-Male, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; phone: 206–231–3992; 

email: Owen.F.Bley-Male@faa.gov. 

(2) Material identified in this AD that is not 

incorporated by reference is available at the 

address specified in paragraph (o)(5) of this 

AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the material listed in this paragraph 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use this material as 

applicable to do the actions required by this 

AD, unless this AD specifies otherwise. 

(3) The following material was approved 

for IBR on November 12, 2024. 

(i) Boeing Alert Service Bulletin 737– 

25A1544, Revision 4, dated February 15, 

2022. 

(ii) [Reserved] 

(4) The following material was approved 

for IBR on February 27, 2009 (74 FR 4117, 

January 23, 2009). 

(i) Boeing Special Attention Service 

Bulletin 737–25–1544, Revision 1, dated 

January 16, 2008. 

(ii) [Reserved] 

(5) For Boeing material identified in this 

AD, contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Blvd., MC 110– 

SK57, Seal Beach, CA 90740–5600; telephone 

562–797–1717; website myboeingfleet.com. 

(6) 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. 

(7) 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 September 6, 2024. 

Peter A. White, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2024–23116 Filed 10–7–24; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1686; Project 

Identifier MCAI–2023–00595–R; Amendment 

39–22839; AD 2024–18–05] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus Helicopters Model AS332C, 

AS332C1, AS332L, AS332L1, and 

SA330J helicopters. This AD was 

prompted by the installation of 

unapproved main gearbox (MGB) 

forward and rear suspension bar 

attachment plates. This AD requires 

inspecting or measuring the MGB 

forward and rear suspension bar 

attachment plates and, depending on 

the results, taking corrective action, 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 November 

12, 2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 12, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1686; 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 EASA AD, 

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; phone: 

+49 221 8999 000; email: ADs@

easa.europa.eu; website: 

easa.europa.eu. You may find the EASA 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material 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. It is also available 

at regulations.gov under Docket No. 

FAA–2024–1686. 

Other Related Material: For Airbus 

Helicopters material identified in this 

AD, contact Airbus Helicopters, 2701 

North Forum Drive, Grand Prairie, TX 

75052; phone: (972) 641–0000 or (800) 

232–0323; fax: (972) 641–3775; or at 

airbus.com/en/products-services/ 

helicopters/hcare-services/airbusworld. 

FOR FURTHER INFORMATION CONTACT: Hye 

Yoon Jang, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (206) 231– 

3758; email: hye.yoon.jang@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 Airbus Helicopters Model 

AS332C, AS332C1, AS332L, AS332L1, 

and SA330J helicopters. The NPRM 

published in the Federal Register on 

June 18, 2024 (89 FR 51468). The NPRM 

was prompted by a series of ADs, the 

most recent being EASA AD 2023–0076, 

dated April 11, 2023 (EASA AD 2023– 

0076), issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition on Airbus Helicopters 

Model SA 330 J, AS 332 C, AS 332 C1, 

AS 332 L, and AS 332 L1 helicopters. 

In the NPRM, the FAA proposed to 

require inspecting or measuring the 

MGB forward and rear suspension bar 

attachment plates and, depending on 

the results, taking corrective action. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 


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