61482 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install an auxiliary motor and pump having 

P/N 782655–3 (Aerocontrolex P/N 4122– 

006009) on any propeller. 

(i) No Return of Parts 

Where the service information referenced 

in the Accomplishment Instructions, 

paragraph 3.B. of Hamilton Sundstrand SB 

14SF–61–168, Revision 1, specifies returning 

certain parts to the manufacturer for 

modification, this AD does not include that 

requirement. 

(j) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (g) of this AD if you 

performed those actions before the effective 

date of this AD using Hamilton Sundstrand 

SB 14SF–61–168, Original Issue, dated 

December 14, 2016. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, East Certification 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 

branch office, send it to the attention of the 

person identified in paragraph (l)(1) of this 

AD. Information may be emailed to: 9-AVSAIR-BACO-COS@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. 

(l) Related Information 

(1) For more information about this AD, 

contact Isabel Saltzman, Aviation Safety 

Engineer, FAA, 1701 Columbia Avenue, 

College Park, GA 30337; phone: (781) 238– 

7649; email: 9-AVS-AIR-BACO-COS@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (4) of this AD. 

(m) 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 the AD specifies otherwise. 

(i) Hamilton Sundstrand Corporation 

Service Bulletin 14SF–61–168, Revision 1, 

dated December 21, 2016. 

Note 2 to paragraph (m)(2)(i): Hamilton 

Sundstrand Corporation is a UTC Aerospace 

Systems Company. This service information 

is identified as both Hamilton Sundstrand 

Corporation and UTC Aerospace Systems. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Hamilton Sundstrand, One 

Hamilton Road, Windsor Locks, CT 06096– 

1010, phone: (877) 808–7575; email: CRC@

collins.com. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, 1200 District 

Avenue, Burlington, MA 01803. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fr.inspection@nara.gov, or go to: 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on August 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–19085 Filed 9–6–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1819; Project 

Identifier MCAI–2023–00052–A] 

RIN 2120–AA64 

Airworthiness Directives; Piaggio 

Aviation S.p.A. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Piaggio Aviation S.p.A. (Piaggio) 

Model P–180 airplanes. This proposed 

AD was prompted by a report of 

corrosion on the various aluminum 

alloy reinforcements in the horizontal 

stabilizer (HS) central box caused by a 

humid environment inside the box from 

water ingress and/or condensation. This 

proposed AD would require a one-time 

detailed inspection of the HS central 

box for corrosion; an assessment of the 

corrosion level; and depending on the 

determination, repetitive detailed 

inspections of the HS central box for 

corrosion and the internal composite 

structure for surface cracks, distortion, 

and damage; and repair or replacement 

of the HS assembly. Repair or 

replacement of the HS assembly would 

be terminating action for the repetitive 

inspections. The FAA is proposing this 

AD to address the unsafe condition on 

these products. 

DATES: The FAA must receive comments 

on this NPRM by October 23, 2023. 

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–2023–1819; 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 NPRM, 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 service information identified 

in this NPRM, contact Piaggio Aviation 

S.p.A., P180 Customer Support, via 

Pionieri e Aviatori d’Italia, snc—16154 

Genoa, Italy; phone: +39 331 679 74 93; 

email: technicalsupport@

piaggioaerospace.it. 

• You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 901 Locust, Kansas City, MO 

64106. For information on the 

availability of this material at the FAA, 

call (817) 222–5110. 

FOR FURTHER INFORMATION CONTACT: 

Sungmo Cho, Aviation Safety Engineer, 

FAA, 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; phone: (781) 238– 

7241; email: sungmo.d.cho@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

The FAA invites you to send any 

written relevant data, views, or 

arguments about this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include ‘‘Docket No. 

FAA–2023–1819; Project Identifier 

MCAI–2023–00052–A’’ at the beginning 

of your comments. The most helpful 

comments reference a specific portion of 

the proposal, explain the reason for any 

recommended change, and include 

supporting data. The FAA will consider 

all comments received by the closing 

date and may amend this proposal 

because of those comments. 

Except for Confidential Business 

Information (CBI) as described in the 

following paragraph, and other 

information as described in 14 CFR 

11.35, the FAA will post all comments 

received, without change, to 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules 61483 

regulations.gov, including any personal 

information you provide. The agency 

will also post a report summarizing each 

substantive verbal contact received 

about this NPRM. 

Confidential Business Information 

CBI is commercial or financial 

information that is both customarily and 

actually treated as private by its owner. 

Under the Freedom of Information Act 

(FOIA) (5 U.S.C. 552), CBI is exempt 

from public disclosure. If your 

comments responsive to this NPRM 

contain commercial or financial 

information that is customarily treated 

as private, that you actually treat as 

private, and that is relevant or 

responsive to this NPRM, it is important 

that you clearly designate the submitted 

comments as CBI. Please mark each 

page of your submission containing CBI 

as ‘‘PROPIN.’’ The FAA will treat such 

marked submissions as confidential 

under the FOIA, and they will not be 

placed in the public docket of this 

NPRM. Submissions containing CBI 

should be sent to Sungmo Cho, Aviation 

Safety Engineer, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 

11590. Any commentary that the FAA 

receives which is not specifically 

designated as CBI will be placed in the 

public docket for this rulemaking. 

Background 

The European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union, has issued EASA AD 

2023–0007, dated January 13, 2023 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition on certain 

serial-numbered Piaggio Model P–180 

airplanes. 

The MCAI states that an occurrence of 

corrosion was found inside the HS 

central box of a Piaggio Model P–180 

airplane during scheduled maintenance. 

A subsequent investigation and 

inspection of 16 other Piaggio Model P– 

180 airplanes of various configurations 

and ages revealed that corrosion of 

differing levels of severity was found on 

various aluminum alloy reinforcements 

in the HS central box of all the 

inspected airplanes. The MCAI also 

states that this corrosion was caused by 

the formation of a humid environment 

inside the HS central box, from water 

ingress and/or condensation. Further 

investigation revealed that airplanes left 

in prolonged inactivity or parked 

outside are more prone to develop 

corrosion damage. 

To address the unsafe condition, the 

MCAI requires a one-time detailed 

inspection of the HS central box for 

corrosion, contacting Piaggio for a 

determination of the corrosion level, 

and depending on that determination, 

repetitive detailed inspections of the HS 

central box for corrosion and the 

internal composite structure for surface 

cracks, distortion, and damage; and 

depending on the results, repair or 

replacement of the HS assembly. The 

MCAI states that repair or replacement 

of the HS assembly is terminating action 

for the repetitive inspections. 

This condition, if not addressed, 

could result in reduced structural 

integrity of the HS, and loss of control 

of the airplane. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1819. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Piaggio Aerospace 

Service Bulletin 80–0489, Revision 2, 

dated November 30, 2022 (Piaggio SB 

80–0489, Revision 2). This service 

information specifies procedures for a 

one-time detailed inspection of the HS 

central box for corrosion, a report of the 

inspection results to Piaggio for a 

determination of the corrosion level, 

repetitive inspections of the HS central 

box as needed, and applicable corrective 

actions. The corrective actions include 

installation of a serviceable HS 

assembly, which is terminating action 

for the repetitive inspections. 

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 ADDRESSES. 

FAA’s Determination 

These products have been approved 

by the aviation authority of another 

country and are 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 and service 

information described above. The FAA 

is issuing this NPRM after determining 

that the unsafe condition described 

previously is likely to exist or develop 

on other products of the same type 

design. 

Proposed AD Requirements in This 

NPRM 

This proposed AD would require 

accomplishing the actions specified in 

the MCAI, except as discussed under 

‘‘Differences Between this Proposed AD 

and the MCAI.’’ 

Differences Between This Proposed AD 

and the MCAI 

The MCAI requires contacting the 

manufacturer for a determination of the 

corrosion level if any corrosion is found 

during the initial inspection of the HS 

central box, and if it is determined that 

level 2 or 3 corrosion is present, having 

the manufacturer provide the threshold 

and intervals for doing repetitive 

inspections of the HS central box. This 

proposed AD would require contacting 

either the FAA, EASA, or Piaggio’s 

EASA Design Organization Approval 

(DOA). If approved by the DOA, the 

approval must include the DOAauthorized signature. 

Although Piaggio SB 80–0489, 

Revision 2, specifies to record the image 

of the location of corroded areas, this 

proposed AD would not require that 

action. 

Costs of Compliance 

The FAA estimates that this AD, if 

adopted as proposed, would affect 102 

airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Initial inspection of HS central box for corrosion.6 work-hours × $85 per hour = $510 ............. $0 $510 $52,020 


ddrumheller on DSK120RN23PROD with PROPOSALS1
61484 Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repetitive inspections of HS central box for corrosion.6 work-hours × $85 per hour = $510, per inspection cycle.$0 $510, per inspection cycle. 

Repetitive inspections for surface cracks, distortion, 

and damage.

6 work-hours × $85 per hour = $510 ....................... 0 $510, per inspection cycle. 

Replace HS assembly .............................................. 10 work-hours × $85 per hour = $850 ..................... 150,000 $150,850. 

The repair of the HS assembly that 

may be required as a result of any 

inspection could vary significantly from 

airplane to airplane. The FAA has no 

data to determine the costs to 

accomplish the repair or the number of 

airplanes that may require the repair. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Would not affect intrastate 

aviation in Alaska, and 

(3) Would 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 Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Piaggio Aviation S.p.A: Docket No. FAA– 

2023–1819; Project Identifier MCAI– 

2023–00052–A. 

(a) Comments Due Date 

The FAA must receive comments on this 

airworthiness directive (AD) by October 23, 

2023. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Piaggio Aviation S.p.A. 

Model P–180 airplanes, serial numbers (S/ 

Ns) 1002, 1004 through 1234 inclusive, 3001 

through 3012 inclusive, and 3016, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 5510, Horizontal Stabilizer Structure. 

(e) Unsafe Condition 

This AD was prompted by a report of 

corrosion on the various aluminum alloy 

reinforcements in the horizontal stabilizer 

(HS) central box caused by a humid 

environment inside the box from water 

ingress and/or condensation. The FAA is 

issuing this AD to address this condition. 

The unsafe condition, if not addressed, could 

result in reduced structural integrity of the 

HS and loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) Within the applicable compliance time 

specified in Table 1 to paragraph (g)(1) of this 

AD, do a detailed inspection of the HS 

central box for corrosion, in accordance with 

step (8), of Part A, of the Accomplishment 

Instructions in Piaggio Aerospace Service 

Bulletin 80–0489, Revision 2, dated 

November 30, 2022 (Piaggio SB 80–0489, 

Revision 2), except you are not required to 

record any images. 

TABLE 1 TO PARAGRAPH (g)(1)—HS CENTRAL BOX ONE TIME INSPECTION

P–180 serial No. 

Compliance time 

(hours time-in-service (TIS) or calendar time, whichever occurs first 

after the effective date of this AD) 

1002; and 1034 through 3016 inclusive ................................................... Within 220 hours TIS or 13 months. 

1004 through 1033 inclusive .................................................................... Within 320 hours TIS or 13 months. 

(2) If, during the inspection required by 

paragraph (g)(1) of this AD, any corrosion is 

detected, before next flight, contact either the 

Manager, International Validation Branch, 

FAA; European Union Aviation Safety 

Agency (EASA); or Piaggio’s EASA Design 

Organization Approval (DOA), for an 

assessment of the corrosion level (level 1, 2, 

or 3). 

Note 1 to paragraph (g)(2): Appendix 1, 

Inspection Results Form, in Piaggio SB 80– 

0489, Revision 2, may be used when 

contacting the FAA, EASA, or Piaggio’s 

EASA DOA. 


ddrumheller on DSK120RN23PROD with PROPOSALS1
Federal Register / Vol. 88, No. 172 / Thursday, September 7, 2023 / Proposed Rules 61485 

(3) If level 1 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, no further action is required by this 

AD. 

(4) If level 2 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, do the action in either paragraph 

(g)(4)(i) or (ii) of this AD. 

(i) Before further flight replace the HS 

assembly or repair the HS assembly in 

accordance with instructions from either the 

Manager, International Validation Branch, 

FAA; EASA; or Piaggio’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(ii) Within 400 hours TIS or 12 months, 

whichever occurs first after the inspection 

required by paragraph (g)(1) of this AD, and 

thereafter at intervals not to exceed 400 hours 

TIS or 12 months, whichever occurs first 

after the most recent inspection, repeat the 

inspection required by paragraph (g)(1) of 

this AD. In addition, inspect the internal 

composite structure of the HS central box for 

surface cracks, distortion, and damage. After 

each repetitive inspection, before further 

flight, assess the inspection findings as 

required by paragraph (g)(2) of this AD. If it 

is determined that the level 2 corrosion has 

worsened since the last inspection; or if any 

surface cracks, distortion, or damage is found 

during any inspection; before further flight, 

replace the HS assembly or repair the HS 

assembly in accordance with instructions 

from either the Manager, International 

Validation Branch, FAA; EASA; or Piaggio’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. These inspections must be 

repeated at intervals not to exceed 400 hours 

TIS or 12 months, whichever occurs first 

after the most recent inspection, until a 

maximum of 660 hours TIS or 13 months, 

whichever occurs first after the inspection 

required by paragraph (g)(1) of this AD has 

been reached, at which time the HS assembly 

must be repaired or replaced. 

(5) If level 3 corrosion is found during the 

inspection required by paragraph (g)(1) of 

this AD, do the actions required by paragraph 

(g)(5)(i) or (ii) of this AD. 

(i) Before further flight after the inspection 

required by paragraph (g)(1) of this AD, 

replace the HS assembly or repair the HS 

assembly in accordance with instructions 

from either the Manager, International 

Validation Branch, FAA; EASA; or Piaggio’s 

EASA DOA. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(ii) Within 200 hours TIS or 6 months, 

whichever occurs first after the inspection 

required by paragraph (g)(1) of this AD, and 

thereafter at intervals not to exceed 200 hours 

TIS or 6 months, whichever occurs first after 

the most recent inspection, repeat the 

inspection required by paragraph (g)(1) of 

this AD. In addition, inspect the internal 

composite structure of the HS central box for 

surface cracks, distortion, and damage. After 

each repetitive inspection, before further 

flight, assess the inspection findings as 

required by paragraph (g)(2) of this AD. If it 

is determined that the level 3 corrosion has 

worsened since the last inspection; or if any 

surface cracks, distortion, or damage is 

found; before further flight, replace the HS 

assembly or repair the HS assembly in 

accordance with instructions from either the 

Manager, International Validation Branch, 

FAA; EASA; or Piaggio’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. These 

inspections must be repeated at intervals not 

to exceed 200 hours TIS or 6 months, 

whichever occurs first after the most recent 

inspection, until a maximum of 660 hours 

TIS or 13 months, whichever occurs first 

after the inspection required by paragraph 

(g)(1) of this AD, at which time the HS 

assembly must be repaired or replaced. 

(6) Repair or replacement of the HS 

assembly is terminating action for the 

repetitive inspections required by paragraphs 

(g)(4)(ii) and (g)(5)(ii) of this AD. 

(h) Credit for Previous Actions 

You may take credit for the actions 

required by paragraphs (g)(1) through (5) of 

this AD if you performed those actions before 

the effective date of this AD using Piaggio 

Aerospace Service Bulletin 80–0489, 

Revision 1, dated May 13, 2022. 

(i) 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 local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, mail it to the address identified in 

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

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

information, also submit information by 

email. 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 

(1) Refer to EASA AD 2023–0007, dated 

January 13, 2023, for related information. 

This EASA AD may be found in the AD 

docket at regulations.gov under Docket No. 

FAA–2023–1819. 

(2) For more information about this AD, 

contact Sungmo Cho, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone: (781) 238– 

7241; email: sungmo.d.cho@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (4) of this AD. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Piaggio Aerospace Service Bulletin 80– 

0489, Revision 2, dated November 30, 2022. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Piaggio Aviation S.p.A., 

P180 Customer Support, via Pionieri e 

Aviatori d’Italia, snc—16154 Genoa, Italy; 

phone: +39 331 679 74 93; email: 

technicalsupport@piaggioaerospace.it. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 901 Locust, 

Kansas City, MO 64106. For information on 

the availability of this material at the FAA, 

call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

email: fr.inspection@nara.gov, or go to: 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued on August 30, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–19092 Filed 9–6–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1816; Project 

Identifier MCAI–2021–01460–R] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH (AHD) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for all 

Airbus Helicopters Deutschland GmbH 

(AHD) Model MBB–BK 117 D–3 

helicopters. This proposed AD was 

prompted by recalculations of the 

inspection intervals for certain parts. 

This proposed AD would require 

revising the airworthiness limitations 

section (ALS) of the existing helicopter 

maintenance manual or instructions for 

continued airworthiness for your 

helicopter and the existing approved 

maintenance or inspection program for 

your helicopter, as applicable, to reduce 

the inspection interval of certain parts, 

as specified in a European Union 

Aviation Safety Agency (EASA) AD, 

which is proposed for incorporation by 

reference (IBR). The FAA is proposing 

this AD to address the unsafe condition 

on these products. 


ddrumheller on DSK120RN23PROD with PROPOSALS1