Federal Register / Vol. 90, No. 26 / Monday, February 10, 2025 / Rules and Regulations 9209 

by the Manager, International Validation 

Branch, FAA; or Transport Canada; or 

Bombardier, Inc.’s Transport Canada Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(i) Additional Information 

For more information about this AD, 

contact Steven Dzierzynski, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; telephone 516– 

228–7300; email 9-avs-nyaco-cos@faa.gov. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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. 

(i) Bombardier Service Bulletin 100–27–22, 

dated December 29, 2022. 

(ii) Bombardier Service Bulletin 350–27– 

012, dated December 29, 2022. 

(3) For Bombardier material identified in 

this AD, contact Bombardier Business 

Aircraft Customer Response Center, 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; phone 514–855–2999; email ac.yul@

aero.bombardier.com; website 

bombardier.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 January 16, 2025. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–02397 Filed 2–7–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1467; Project 

Identifier AD–2023–01241–T; Amendment 

39–22935; AD 2025–02–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 737–100, –200, 

–200C, –300, –400, and –500 series 

airplanes. This AD was prompted by a 

report indicating cracks in the frame 

inner chord and web at station (STA) 

727. This AD requires an inspection for 

any repair installed, repetitive 

inspections of the frame inner chord 

and web at STA 727 for any crack, and 

applicable on-condition actions. The 

FAA is issuing this AD to address the 

unsafe condition on these products. 

DATES: This AD is effective March 17, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 17, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1467; 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 

Boulevard, 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 Street, Des Moines, WA. For 

information on the availability of this 

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

It is also available at regulations.gov 

under Docket No. FAA–2024–1467. 

FOR FURTHER INFORMATION CONTACT: 

Muoi Vuong, Aviation Safety Engineer, 

FAA, 2200 South 216th Street, Des 

Moines, WA 98198; telephone: 562– 

627–5205; email: Muoi.Vuong@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. The NPRM 

published in the Federal Register on 

May 20, 2024 (89 FR 43792). The NPRM 

was prompted by a report indicating 

cracks in the frame inner chord and web 

at STA 727 between S–11L and S–13L. 

In the NPRM, the FAA proposed to 

require an inspection for any repair 

installed, repetitive inspections of the 

frame inner chord and web at STA 727 

for any crack, and applicable oncondition actions. The FAA is issuing 

this AD to address cracks in the left and 

right frames at STA 727 before they 

reach a critical length. The unsafe 

condition, if not addressed, may result 

in the inability of a principal structural 

element to sustain limit load, which 

could adversely affect the structural 

integrity of the airplane. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from 

three commenters, including Aviation 

Partners Boeing, FlyPersia Airline, and 

Sudan Civil Aviation Authority. In 

addition, the FAA received a comment 

from an individual whose request is not 

specific to this AD or a request the FAA 

can act on. This comment is outside the 

scope of this rulemaking. The following 

presents the comments received on the 

NPRM and the FAA’s response to each 

comment. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

the installation of winglets per the 

Supplemental Type Certificate (STC) 

ST01219SE does not affect the actions 

specified in the proposed AD. 

The FAA agrees with the commenter. 

The FAA has redesignated paragraph (c) 

of the proposed AD as paragraph (c)(1) 

of this AD and added paragraph (c)(2) to 

this AD to state that installation of STC 

ST01219SE does not affect the ability to 

accomplish the actions required by this 

AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change 

in product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Expand the Area of 

Inspection 

FlyPersia Airline requested that the 

area of inspection for any repair and 

repetitive high frequency eddy current 

inspection include the frame inner 

chord and web at STA 663.75 through 

STA 727 between stringers S–11 and S– 

13 left and right sides. The commenter 

stated that the mentioned crack on 

stringers S–11 and S–13 left and right 

might also exist on those stringers at 

STA 663.75 through STA 727, because 

on Model 737–300 airplanes there is a 

landing gear cavity, which impresses 

circumferential structure unity on STA 

663.75. 


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9210 Federal Register / Vol. 90, No. 26 / Monday, February 10, 2025 / Rules and Regulations 

The FAA disagrees with expanding 

the area of inspection in this AD. The 

Boeing service bulletin addresses only 

the frame inner chord and web at STA 

727, between S–11 and S–13, left and 

right sides. STA 727 frame between S– 

11 and S–13, located at a bulkhead 

station, is different from other frames 

forward of STA 727, and therefore is the 

only area of inspection addressed in this 

AD. However, if additional data are 

presented that would justify extending 

the subject inspection area, the FAA 

might consider further rulemaking on 

this issue. No change has been made to 

this AD regarding this issue. 

Request To Reduce the Proposed Grace 

Period for the Initial Compliance Time 

Sudan Civil Aviation Authority 

requested the grace period for the initial 

compliance time for the general visual 

inspection of STA 727 (within 4,500 

flight cycles after the original issue date 

of the requirements bulletin) be 

reduced. Sudan Civil Aviation 

Authority stated that the compliance 

time for some Model 737–400 airplanes 

may fall beyond the 50,000 total flight 

cycles at which the crack has been 

found. 

The FAA disagrees. After considering 

all the available information, the FAA 

has determined that the grace period, as 

proposed, represents an appropriate 

interval of time in which the required 

actions can be performed in a timely 

manner within the affected fleet, while 

still maintaining an adequate level of 

safety. In developing an appropriate 

grace period, the FAA considered the 

safety implications, parts availability, 

normal maintenance schedules, and the 

manufacturer’s recommendation for 

timely accomplishment of the 

modifications. To reduce the grace 

period of the proposed AD would 

necessitate (under the provisions of the 

Administrative Procedure Act) reissuing 

the notice, reopening the period for 

public comment, considering additional 

comments subsequently received, and 

eventually issuing a final rule. In light 

of this, and in consideration of the 

amount of time that has already elapsed 

since issuance of the original notice, the 

FAA has determined that further delay 

of this AD is not appropriate. However, 

if additional data are presented that 

would justify a shorter compliance time, 

the FAA may consider further 

rulemaking on this issue. No change has 

been made to this AD regarding this 

issue. 

Request To Revise Requirements 

Bulletin To Delete Condition 2.2 

Sudan Civil Aviation Authority stated 

that Condition 2.2: No Crack Found in 

Group 2, Table 1: Inspection of Frame 

at STA 727 Between S–11 and S–13, 

Left and Right Side, 3. Compliance, of 

Boeing Alert Requirements Bulletin 

737–53A1416RB, dated July 21, 2023, 

needs to be deleted. The commenter 

pointed out that Condition 2.2 

(unrepaired areas) should be deleted 

because there is no repair found. 

The FAA agrees to clarify. Condition 

2 is accomplished for airplanes that 

have no repairs in the inspection area 

and requires high frequency eddy 

current (HFEC) inspections of the area 

before further flight. Condition 2.2 is 

then accomplished if no crack is found 

during the initial inspection (Condition 

2), repeating the HFEC inspections of 

the unrepaired areas within 9,000 flight 

cycles. Condition 2.2 includes footnote 

(a) because a repair could be installed at 

any point prior to the repeat HFEC 

inspection, and that repair could 

terminate the repeat HFEC inspection. 

No change has been made to this AD 

regarding this issue. 

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 

Requirements Bulletin 737–53A1416 

RB, dated July 21, 2023. This material 

specifies procedures for a general visual 

inspection for any repair and repetitive 

high frequency eddy current inspections 

of the frame inner chord and web at 

STA 727, between S–11 and S–13, left 

and right sides, for any crack, and 

applicable on-condition actions. Oncondition actions include obtaining and 

following repair instructions. This 

material is reasonably available because 

the interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 245 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 

Inspections ............................. 8 work-hours × $85 per hour = $680 ..................................... $0 $680 $166,600 

The FAA has received no definitive 

data on which to base the cost estimates 

for the on-condition actions 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: 


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Federal Register / Vol. 90, No. 26 / Monday, February 10, 2025 / Rules and Regulations 9211 

(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 adding 

the following new airworthiness 

directive: 

2025–02–02 The Boeing Company: 

Amendment 39–22935; Docket No. 

FAA–2024–1467; Project Identifier AD– 

2023–01241–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 17, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE does not affect 

the ability to accomplish the actions required 

by this AD. Therefore, for airplanes on which 

STC ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report 

indicating cracks in the frame inner chord 

and web at station (STA) 727. The FAA is 

issuing this AD to address cracks in the left 

and right frames at STA 727 before they 

reach a critical length. The unsafe condition, 

if not addressed, may result in the inability 

of a principal structural element to sustain 

limit load, which could adversely affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions for Group 1 Airplanes 

For airplanes identified as Group 1 in 

Boeing Alert Requirements Bulletin 737– 

53A1416 RB, dated July 21, 2023: Within 120 

days after the effective date of this AD, 

inspect for existing repairs and cracking of 

the frame inner chord and web at STA 727, 

between S–11 and S–13, left and right sides, 

using a method approved in accordance with 

the procedures specified in paragraph (j) of 

this AD. 

(h) Required Actions for Group 2 Airplanes 

For airplanes identified as Group 2 in 

Boeing Alert Requirements Bulletin 737– 

53A1416 RB, dated July 21, 2023: Except as 

specified by paragraph (i) of this AD, at the 

applicable times specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 737–53A1416 RB, 

dated July 21, 2023, do all applicable actions 

identified in, and in accordance with, the 

Accomplishment Instructions of Boeing Alert 

Requirements Bulletin 737–53A1416 RB, 

dated July 21, 2023. 

Note 1 to paragraph (h): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Service Bulletin 

737–53A1416, dated July 21, 2023, which is 

referred to in Boeing Alert Requirements 

Bulletin 737–53A1416 RB, dated July 21, 

2023. 

(i) Exceptions to Requirements Bulletin 

Specifications 

(1) Where the Compliance Time columns 

of the tables in the ‘‘Compliance’’ paragraph 

of Boeing Alert Requirements Bulletin 737– 

53A1416 RB, dated July 21, 2023, refers to 

the original issue date of Boeing Alert 

Requirements Bulletin 737–53A1416 RB, this 

AD requires using the effective date of this 

AD. 

(2) Where Boeing Alert Requirements 

Bulletin 737–53A1416 RB, dated July 21, 

2023, specifies contacting Boeing for repair 

instructions or for alternative inspections, 

this AD requires doing the repair, or doing 

the alternative inspections and applicable oncondition actions, before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (j) of this 

AD. 

(j) Alternative Methods of Compliance 

(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 the certification office, 

send it to the attention of the person 

identified in paragraph (k)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Muoi Vuong, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, Des 

Moines, WA 98198; telephone: 562–627– 

5205; email: Muoi.Vuong@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 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 

737–53A1416 RB, dated July 21, 2023. 

(ii) [Reserved] 

(3) For Boeing material identified in this 

AD, contact Boeing Commercial Airplanes, 

Attention: Contractual & Data Services 

(C&DS), 2600 Westminster Boulevard, 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 Street, Des 

Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

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

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

Issued on January 14, 2025. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02383 Filed 2–7–25; 8:45 am] 

BILLING CODE 4910–13–P 


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