8658 Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Rules and Regulations 

2025–03–02 Airbus Helicopters: 

Amendment 39–22950; Docket No. 

FAA–2024–2332; Project Identifier 

MCAI–2022–01479–R. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 7, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Helicopters 

AS332C, AS332C1, AS332L, AS332L1, 

AS332L2, AS355E, AS355F, AS355F1, 

AS355F2, AS355N, AS355NP, AS–365N2, 

AS 365 N3, EC 155B, EC155B1, EC225LP, 

SA–365N, and SA–365N1 helicopters, 

certificated in any category, with a collective 

pitch handle installed on a pilot or co-pilot 

collective stick having part number (P/N) 

704A41–1100–42, 704A41–1100–50, 

704A41–1100–56, 704A41–1100–57, 

704A41–1100–60, 704A41–1100–67, 

704A41–1100–68, 704A41–1100–97, 

704A41–1100–98, 704A41–1100–99, 

704A41–1101–14, 704A41–1101–30, or 

704A41–1101–32, installed, as applicable to 

the model helicopter. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2510, Flight compartment equipment. 

(e) Unsafe Condition 

This AD was prompted by a report of an 

unintentional activation of the hoist shearbutton (shear-button) on the collective pitch 

handle during a night flight. The FAA is 

issuing this AD to detect and address fatigue 

of the spring in the shear-button safety-cap 

on the left and right collective pitch handles. 

The unsafe condition, if not addressed, could 

result in an unintended shearing of the hoist 

cable and subsequent injury to the hoisted 

person. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For helicopters identified in paragraph 

(c) of this AD that have a hoist installed, 

within 50 hours time-in-service (TIS) after 

the effective date of this AD, and thereafter 

at intervals not to exceed 12 months TIS, 

check the operation of the shear-button 

safety-cap on each applicable collective pitch 

handle by accomplishing the actions required 

by paragraphs (g)(1)(i) through (iii) of this 

AD, as applicable. The owner/operator (pilot) 

holding at least a private pilot certificate may 

perform the checks required by paragraphs 

(g)(1)(i) through (iii) of this AD and must 

enter compliance with these paragraphs into 

the helicopter maintenance records in 

accordance with 14 CFR 43.9(a) and 

91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(i) Place your thumb under the safety-cap 

and lift the safety-cap to a less-than halfway 

position. Remove your thumb and verify that 

the safety-cap goes to the fully open position 

or that the safety-cap returns to the fully 

closed position. Repeat these actions no less 

than two more times. If the safety-cap stays 

in the less-than halfway position, or the 

safety-cap does not fully close or fully open 

during any instance of the actions required 

by this paragraph, before further flight, a 

person authorized under 14 CFR 43.3 must 

accomplish the actions required by paragraph 

(g)(2) of this AD. 

(ii) Place your thumb under the safety-cap 

and lift the safety-cap to a halfway position. 

Remove your thumb and verify that the 

safety-cap goes to the fully open position or 

that the safety-cap returns to the fully closed 

position. Repeat these actions no less than 

two more times. If the safety-cap stays in the 

halfway position, or the safety-cap does not 

fully close or fully open during any instance 

of the actions required by this paragraph, 

before further flight, a person authorized 

under 14 CFR 43.3 must accomplish the 

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

AD. 

(iii) Place your thumb under the safety-cap 

and lift the safety-cap to a more-than halfway 

position. Remove your thumb and verify the 

safety-cap goes to the fully open position or 

that the safety-cap returns to the fully closed 

position. Repeat these actions no less than 

two more times. If the safety-cap stays in the 

more-than halfway position, or the safety-cap 

does not fully close or fully open during any 

instance of the actions required by this 

paragraph, before further flight, a person 

authorized under 14 CFR 43.3 must 

accomplish the actions required by paragraph 

(g)(2) of this AD. 

(2) If the safety-cap stays in the less-than 

halfway, halfway, or more-than halfway 

position, or the safety-cap does not fully 

close or fully open during any instance of the 

actions required by paragraphs (g)(1)(i) 

through (iii) of this AD, before further flight, 

remove the spring from service and replace 

it with an airworthy spring. 

(3) As an alternative to replacing the spring 

as required by paragraph (g)(2) of this AD, 

accomplish the actions required by 

paragraphs (g)(3)(i) and (ii) of this AD. 

(i) Before further flight, fabricate a placard 

with a font size greater than or equal to 4 mm 

(.157 in), stating the following: ‘‘NIGHT 

HOIST OPERATIONS PROHIBITED.’’ The 

placard must have a red background with 

white font color or a white background with 

red font color. The placard must not be 

erasable and must be attached to the 

instrument panel, visible to the pilot and copilot. 

(ii) Within 150 hours TIS after 

accomplishing the actions required by 

paragraph (g)(3)(i) of this AD, remove the 

spring of the safety-cap from service and 

replace it with an airworthy spring, and 

remove the placard from service. 

(4) For helicopters identified in paragraph 

(c) of this AD that do not have a hoist 

installed, before installation of a hoist’s 

removable parts on the helicopter, 

accomplish the check and as applicable, 

corrective action, required by paragraphs 

(g)(1) through (3) of this AD. 

(h) Parts Installation Limitations 

As of the effective date of this AD, do not 

install on any helicopter a collective pitch 

handle having a P/N identified in paragraph 

(c) of this AD, or any pilot or co-pilot 

collective stick with a collective pitch handle 

having a P/N identified in paragraph (c) of 

this AD installed, unless the check and as 

applicable, corrective action, required by 

paragraphs (g)(1) through (3) of this AD have 

been done or the collective pitch handle is 

new (zero total hours TIS). 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, send it to the attention of the person 

identified in paragraph (j) 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 local flight standards district office/ 

certificate holding district office. 

(j) Additional Information 

For more information about this AD, 

contact Dan McCully, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (404) 474– 

5548; email: william.mccully@faa.gov. 

(k) Material Incorporated by Reference 

None. 

Issued on January 27, 2025. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2025–02027 Filed 1–30–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–1699; Project 

Identifier AD–2023–01084–T; Amendment 

39–22918; AD 2024–26–03] 

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 certain 

The Boeing Company Model 767–200, 

–300, and –400ER series airplanes. This 

AD was prompted by a report of 

multiple engine indicating and crew 

alerting system messages during potable 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Rules and Regulations 8659 

water servicing after the water leaked 

onto the electronics equipment cooling 

air filter. This AD requires installation 

of hoseducts around the left-side section 

43 potable water supply hoses and 

connections, a potable water system 

leakage test, and applicable corrective 

actions. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective March 7, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 7, 2025. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–1699; 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–2024–1699. 

FOR FURTHER INFORMATION CONTACT: 

Courtney Tuck, Aviation Safety 

Engineer, FAA, 2200 South 216th St., 

Des Moines, WA 98198; phone: 206– 

231–3986; email: Courtney.K.Tuck@

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 certain The Boeing Company 

Model 767–200, –300, and –400ER 

series airplanes. The NPRM published 

in the Federal Register on June 26, 2024 

(89 FR 53367). The NPRM was 

prompted by a report of multiple engine 

indicating and crew alerting system 

messages during the potable water 

servicing for a Model 777 freighter 

airplane. The cause was found to be the 

separation of a fitting and steel water 

supply tube at a location above an 

electronics equipment cooling air filter, 

behind the forward cargo compartment 

left sidewall. The water from the soaked 

filter was then blown by the equipment 

cooling system onto multiple line 

replaceable units in the main electronics 

center. Model 767 passenger airplanes 

are similar in design to Model 777 

freighter airplane. In the NPRM, the 

FAA proposed to require installation of 

hoseducts around the left-side section 

43 potable water supply hoses and 

connections, a potable water system 

leakage test, and applicable corrective 

actions. The FAA is issuing this AD to 

address water leakage from the potable 

water system near the equipment 

cooling supply air inlet. The unsafe 

condition, if not addressed, could 

damage main electronics center 

components and result in loss of 

continued safe flight and landing. 

Related Rulemaking 

To address the identified unsafe 

condition on Model 777F series 

airplanes, the FAA issued AD 2021–06– 

03, Amendment 39–21469 (86 FR 

12809, March 5, 2021), as an interim 

action that required deactivation of the 

potable water system. The FAA 

followed with AD 2022–23–10, 

Amendment 39–22237 (87 FR 73448, 

November 30, 2022). 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA), Boeing, and 

United Airlines (UAL), who supported 

the NPRM without change. 

The FAA received additional 

comments from Aviation Partners 

Boeing (APB), Delta Air Lines (Delta), 

United Parcel Service Co. (UPS 

Airlines), and Air Canada. 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 

APB stated that the installation of 

winglets per Supplemental Type 

Certificate (STC) ST01920SE does not 

affect compliance with the proposed 

actions. 

The FAA agrees with the commenter. 

The installation of STC ST01920SE does 

not affect the ability to accomplish the 

actions required by this AD. The FAA 

has not changed this AD in this regard. 

Request To Correct a Part Name in 

Boeing Service Bulletin 

Delta requested that the FAA add an 

exception to paragraph (h) of the 

proposed AD as follows: Where the 

‘‘Name’’ column for P/N NAS43DD6– 

24FC in step 5 of figure 11 and step 5 

of figure 13 in Boeing Alert 

Requirements Bulletin 767–38A0076 

RB, dated December 1, 2023, states 

‘‘SPACERS FOR BOLTS,’’ this AD 

requires using ‘‘SPACER FOR BOLT.’’ 

Only one spacer needs to be installed. 

The FAA agrees with the request. 

Only one spacer is to be installed in step 

5 of figure 11 and step 5 of figure 13. 

The FAA has added paragraph (h)(2) to 

this AD accordingly. 

Requests for Excluding Boeing Model 

767–300 Bedek Special Freighters in 

Applicability 

UPS Airlines requested that the FAA 

add the following statement to this AD: 

‘‘This AD is not applicable to 767–300 

airplanes listed in the Boeing Alert 

Requirements Bulletin 767–38A0076 

RB, dated December 1, 2023, that were 

converted by Israel Aerospace Industries 

(IAI) STC number ST02040SE to 

freighter configuration where the subject 

hoses were removed.’’ UPS Airlines 

stated that it operates Boeing Model 

767–300 series airplanes converted to 

freighter configuration by IAI, known as 

767–300 Bedek Special Freighter (BDSF) 

fleet. The potable water hoses indicated 

in the Boeing service bulletin have been 

removed during freighter conversion by 

IAI STC number ST02040SE to freighter 

configuration. 

Similarly, Air Canada requested that 

the FAA add a statement stating that 

this AD is not applicable to any Boeing 

Model 767–300 passenger airplanes 

listed in Boeing Alert Requirements 

Bulletin 767–38A0076 RB, dated 

December 1, 2023, that have been 

modified to a 767–300BDSF 

configuration. Air Canada operates six 

Model 767–300 airplanes that were 

modified to an all-cargo configuration as 

per IAI STC ST02040SE. During this 

modification the water system was 

removed similar to the Boeing Model 

767–300 converted freighter airplanes. 

The FAA agrees with the requests. 

The potable water hoses indicated in 

Boeing Alert Requirements Bulletin 

767–38A0076 RB, dated December 1, 

2023, have been removed during 

freighter conversion by IAI STC number 

ST02040SE to freighter configuration. 

The FAA has revised paragraph (c) of 

this AD accordingly. 

Conclusion 

The FAA reviewed the relevant data, 

considered any comments received, and 


ddrumheller on DSK120RN23PROD with RULES1
8660 Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Rules and Regulations 

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 767–38A0076 

RB, dated December 1, 2023. This 

material specifies procedures for the 

following actions at the lower lobe 

section 43 potable water system 

plumbing on the left-side: 

• Installing hoseducts and support 

clamps. 

• Installing spray shields, new tie 

straps on the supply hose, and tee fitting 

shrouds, depending on the airplane 

configuration. 

• Replacing the supply hoses and tee 

fittings for certain airplane 

configurations. 

• Doing a potable water system 

leakage test and, for any leakage found, 

repeating the test until no leakage is 

found. 

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 397 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 

Install hose ducts, connections, and leakage test.Up to 19 work-hours × $85 

per hour = $1,615.

Up to $1,130 Up to $2,745 ........................... Up to $1,089,765. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some or all 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected operators. 

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 adding 

the following new airworthiness 

directive: 

2024–26–03 The Boeing Company: 

Amendment 39–22918; Docket No. 

FAA–2024–1699; Project Identifier AD– 

2023–01084–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective March 7, 2025. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 767–200, –300, and –400ER series 

airplanes, as identified in Boeing Alert 

Requirements Bulletin 767–38A0076 RB, 

dated December 1, 2023, excluding the 

airplanes that were converted by STC 

number ST02040SE to freighter configuration 

where the subject hoses were removed. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 38, Water/waste. 

(e) Unsafe Condition 

This AD was prompted by a report of 

multiple engine indicating and crew alerting 

system messages during potable water 

servicing after the water leaked onto the 

electronics equipment cooling air filter. The 

FAA is issuing this AD to address water 

leakage from the potable water system near 

the equipment cooling supply air inlet. The 

unsafe condition, if not addressed, could 

damage main electronics center components 

and result in loss of continued safe flight and 

landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

Except as specified by paragraph (h) of this 

AD: At the applicable time specified in the 

‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 767–38A0076 RB, 

dated December 1, 2023, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin 767–38A0076 

RB, dated December 1, 2023. 

Note 1 to paragraph (g): Guidance for 

accomplishing the actions required by this 

AD can be found in Boeing Alert Service 

Bulletin 767–38A0076, dated December 1, 

2023, which is referred to in Boeing Alert 


ddrumheller on DSK120RN23PROD with RULES1
Federal Register / Vol. 90, No. 20 / Friday, January 31, 2025 / Rules and Regulations 8661 

Requirements Bulletin 767–38A0076 RB, 

dated December 1, 2023. 

(h) Exceptions to Service Information 

Specifications 

(1) Where the Boeing Recommended 

Compliance Time columns of the tables in 

the ‘‘Compliance’’ paragraph of Boeing Alert 

Requirements Bulletin 767–38A0076 RB, 

dated December 1, 2023, refer to ‘‘the 

Original Issue date of Requirements Bulletin 

767–38A0076 RB,’’ this AD requires using 

the effective date of this AD. 

(2) Where step 5 of figures 11 and 13 in 

Boeing Alert Requirements Bulletin 767– 

38A0076 RB, dated December 1, 2023, refers 

to the part name ‘‘spacers for bolts,’’ this AD 

requires replacing that text with ‘‘spacer for 

bolt.’’ 

(i) 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 the certification office, 

send it to the attention of the person 

identified in paragraph (j)(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. 

(j) Related Information 

(1) For more information about this AD, 

contact Courtney Tuck, Aviation Safety 

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

Moines, WA 98198; phone: 206–231–3986; 

email: Courtney.K.Tuck@faa.gov. 

(2) Material identified in this AD that is not 

incorporated by reference is available at the 

address specified in paragraph (k)(3) this AD. 

(k) 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 material as 

applicable to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Boeing Alert Requirements Bulletin 

767–38A0076 RB, dated December 1, 2023. 

(ii) [Reserved] 

(3) 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. 

(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 December 19, 2024. 

Suzanne Masterson, 

Deputy Director, Integrated Certificate 

Management Division, Aircraft Certification 

Service. 

[FR Doc. 2025–02040 Filed 1–30–25; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2024–2664; Project 

Identifier MCAI–2024–00518–E; Amendment 

39–22912; AD 2024–25–10] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) Model Trent XWB–97 engines. 

This AD was prompted by a report of 

damage to the main fuel hose assembly 

of the fuel manifold, which resulted an 

in-flight shut down. This AD requires a 

one-time set of visual and dimensional 

inspections of the main fuel hose 

assembly of the fuel manifold to confirm 

softness, compliance, and lack of 

resistance, and for shrinkage, cracks, 

chafing, dents, kinks, necking, and 

degradation of the hose braid wire; and, 

if necessary, replacement of the main 

fuel hose assembly of the fuel manifold, 

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 February 18, 

2025. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 18, 2025. 

The FAA must receive comments on 

this AD by March 17, 2025. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

regulations.gov. Follow the instructions 

for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2024–2664; 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 street address for 

Docket Operations is listed above. 

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 this 

material on the EASA website at 

ad.easa.europa.eu. 

• You may view this material at the 

FAA, Operational Safety Branch, 1200 

District Avenue, Burlington, MA 01803. 

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– 

2024–2664. 

FOR FURTHER INFORMATION CONTACT: 

Barbara Caufield, Aviation Safety 

Engineer, FAA, 2200 South 216th Street, 

Des Moines, WA 98198; phone: (781) 

238–7146; email: barbara.caufield@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written data, views, or arguments about 

this final rule. Send your comments to 

an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2024–2664; 

Project Identifier MCAI–2024–00518–E’’ 

at the beginning of your comments. The 

most helpful comments reference a 

specific portion of the final rule, explain 

the reason for any recommended 


ddrumheller on DSK120RN23PROD with RULES1