67636 Federal Register / Vol. 88, No. 189 / Monday, October 2, 2023 / Rules and Regulations 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 2000, Airframe. 

(e) Unsafe Condition 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as corrosionrelated degradation in aging aircraft. The 

FAA is issuing this AD to detect and address 

corrosion, which could lead to structural 

failure with consequent 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 90 days after the effective date 

of this AD, incorporate into the existing 

maintenance records required by 14 CFR 

91.417(a)(2) or 135.439(a)(2), as applicable 

for your airplane, the actions and associated 

thresholds and intervals, including life 

limits, specified in Parts 2 and 3 of Viking 

DHC–2 Beaver Supplemental Inspection and 

Corrosion Control Manual, PSM 1–2–5, 

Revision 1, dated January 10, 2019 (Viking 

PSM 1–2–5, Revision 1). Do each initial task 

within 6 months after the effective date of 

this AD or at the threshold for each 

applicable task specified in Part 3 of Viking 

Product Support Manual PSM 1–2–5, 

Revision 1, whichever occurs later. Where 

Viking PSM 1–2–5, Revision 1, specifies 

contacting Viking for instructions on forward 

and rear fin attachment bolt replacement, 

inspection, and installation, and for a 

disposition regarding attachment bolts, this 

AD requires contacting the Manager, 

International Validation Branch, FAA; or 

Transport Canada; or Viking’s Transport 

Canada Design Approval Organization 

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

must include the DAO-authorized signature. 

Note 1 to paragraph (g)(1): Viking DHC–2 

Beaver Service Bulletin V2/0011, Revision 

NC, dated November 28, 2019, contains 

additional information related to this AD. 

(2) After the action required by paragraph 

(g)(1) of this AD has been done, no 

alternative actions and associated thresholds 

and intervals, including life limits, are 

allowed unless they are approved as 

specified in paragraph (i) of this AD. 

(h) Reporting 

(1) For inspections done after the effective 

date of this AD, report to Viking any Level 

2 or Level 3 corrosion, as specified in Viking 

PSM 1–2–5, Revision 1, at the times specified 

in and in accordance with part 3, paragraph 

5, of Viking PSM 1–2–5, Revision 1. 

(2) For inspections done before the 

effective date of this AD, within 30 days after 

the effective date of this AD, report to Viking 

any Level 2 or Level 3 corrosion, as specified 

in Viking PSM 1–2–5, Revision 1, in 

accordance with part 3, paragraph 5, of 

Viking PSM 1–2–5, Revision 1. 

(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, mail it to ATTN: Program Manager, 

Continuing Operational Safety, at 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. 

(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. 

(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 specifically for this AD 

by the Manager, International Validation 

Branch, FAA. 

(j) Additional Information 

(1) Refer to the MCAI from Transport 

Canada, AD CF–2019–25, dated July 5, 2019, 

for related information. This Transport 

Canada AD may be found in the AD docket 

at regulations.gov under Docket No. FAA– 

2022–0190. 

(2) For more information about this AD, 

contact James Delisio, Continued Operational 

Safety Program Manager, FAA, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

phone: (516) 228–7321; email: 9-avs-nyacocos@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) Viking DHC–2 Beaver Supplemental 

Inspection and Corrosion Control Manual, 

PSM 1–2–5, Revision 1, dated January 10, 

2019. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Viking Air Limited 

Technical Support, 1959 De Havilland Way, 

Sidney, British Columbia, Canada, V8L 5V5; 

phone: (800) 663–8444; fax: (250) 656–0673; 

email: technical.support@vikingair.com; 

website: vikingair.com/support/servicebulletins. 

(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 September 15, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–21631 Filed 9–29–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0674; Project 

Identifier AD–2021–00373–T; Amendment 

39–22559; AD 2023–19–09] 

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) 2020–24– 

04, which applied to all The Boeing 

Company Model 787–8, 787–9, and 

787–10 airplanes. AD 2020–24–04 

required revising the existing airplane 

flight manual (AFM) to incorporate 

procedures for an approach with a 

localizer-based navigation aid, 

monitoring localizer raw data, calling 

out any significant deviations, and 

performing an immediate go around 

under certain conditions. This AD was 

prompted by the development of a 

modification to address the previously 

identified unsafe condition, and the 

identification of a separate unsafe 

condition where misleading vertical 

flight director (FD) guidance can be 

presented to the flightcrew under 

certain conditions. This AD continues to 

require the actions specified in AD 

2020–24–04 and requires installing 

applicable software updates to the flight 

control module (FCM). Using updated 

software terminates the retained AFM 

requirement in this AD. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 6, 

2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 6, 2023. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 


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No. FAA–2022–0674; 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 service information identified 

in this final rule, 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 service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available at 

regulations.gov under Docket No. FAA– 

2022–0674. 

FOR FURTHER INFORMATION CONTACT: 

Doug Tsuji, Aviation Safety Engineer, 

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

WA 98198; phone: 206–231–3548; 

email: Douglas.Tsjui@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2020–24–04, 

Amendment 39–21334 (85 FR 77991, 

December 3, 2020; corrected December 

14, 2020 (85 FR 80589)) (AD 2020–24– 

04). AD 2020–24–04 applied to all The 

Boeing Company Model 787–8, 787–9, 

and 787–10 airplanes. The NPRM 

published in the Federal Register on 

June 29, 2022 (87 FR 38682). The NPRM 

was prompted by reports indicating that 

the autopilot flight director system 

(AFDS) failed to transition to the 

instrument landing system localizer 

(LOC) beam after the consistent localizer 

capture function in the FCMs initiated 

a transition to capture LOC during 

approach, and the manufacturer’s 

development of a modification to 

address this unsafe condition. The 

NPRM was also prompted by the 

identification of a separate unsafe 

condition where misleading vertical FD 

guidance can be presented to the 

flightcrew under certain conditions. In 

the NPRM, the FAA proposed to 

continue to require the actions specified 

in AD 2020–24–04 and to require 

installing applicable software updates to 

the FCM. Installing updated software 

terminates the retained AFM 

requirement in this AD. The FAA is 

issuing this AD to address the AFDS 

failing to transition, which could result 

in localizer overshoot leading to 

glideslope descent on the wrong 

heading. Combined with a lack of flight 

deck effects for a consistent localizer 

capture mode failure, this condition 

could result in a controlled flight into 

terrain (CFIT). The NPRM was further 

prompted by reports of misleading 

vertical flight director guidance that in 

certain scenarios can be presented to the 

flightcrew during approach and could 

lead to CFIT or a runway overrun. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from the 

Air Line Pilots Association, 

International (ALPA), who supported 

the NPRM without change. 

The FAA received additional 

comments from two commenters, 

including Boeing and an individual. 

The following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Request To Remove Certain Line 

Numbers From the Applicability 

Boeing requested that the proposed 

AD be revised to remove line numbers 

1062 and 1076 from the applicability. 

Boeing noted that those airplanes would 

have the requirements of B787–81205– 

SB270053–00 RB, Issue 002, dated May 

6, 2021, incorporated during 

production. 

The FAA agrees with the intent of the 

commenter’s request. The FAA has 

added paragraph (j)(2) of this AD to 

specify that for airplanes on which 

Common Block Point (CBP) 5.1, 27 FCM 

Operational Program Software (OPS) 

part number HNP5A–AL01–5041 or 

later-approved software part number is 

installed on FCM–L, FCM–C, and FCM– 

R during production, the actions 

specified in paragraph (h) of this AD are 

not required. Additionally, the FAA has 

revised paragraph (g) of this AD to apply 

only to airplanes on which CBP 5.1, 27 

FCM OPS part number HNP5A–AL01– 

5041 or later approved software part 

number is not installed on FCM–L, 

FCM–C, and FCM–R. Finally, the FAA 

has revised paragraph (k) of this AD to 

specify that installation of CBP 5.1, 27 

FCM OPS part number HNP5A–AL01– 

5041 or later-approved software part 

number on FCM–L, FCM–C, and FCM– 

R in production terminates the AFM 

revision required by paragraph (g) of 

this AD. Since some airplanes had this 

software installed during production, 

the FAA has determined that revision of 

the existing AFM required by paragraph 

(g) of this AD is not applicable to those 

airplanes. 

Request To Allow Additional 

Terminating Action 

An individual requested that the FAA 

clarify whether accomplishing the 

actions in Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, 

Issue 001, dated February 19, 2021, 

terminates the AFM revision required 

by paragraph (g) of the proposed AD. 

The commenter noted that paragraph 

(l)(1) of the proposed AD provides credit 

for previous accomplishment of Boeing 

Alert Requirements Bulletin B787– 

81205–SB270053–00 RB, Issue 001, 

dated February 19, 2021, but does not 

specify whether that credit extends to 

the terminating actions specified in 

paragraph (k) of the proposed AD. 

The FAA agrees to clarify. The FAA 

has revised paragraph (l)(1) of this AD 

to specify that the credit applies to the 

actions in both paragraphs (h) and (k) of 

this AD. Therefore, accomplishing the 

actions in Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, 

Issue 001, dated February 19, 2021, 

terminates the AFM revision required 

by paragraph (g) of the proposed AD, 

provided the software update has been 

installed on all affected airplanes in an 

operator’s fleet. 

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. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Boeing Alert 

Requirements Bulletin B787–81205– 

SB270053–00 RB, Issue 002, dated May 

6, 2021. This service information 

specifies procedures for updating flight 

control electronics (FCE) software to 

install CBP 5.1 OPS having part number 

HNP5A–AL01–5041 in the FCM, and 

doing a software configuration check. 

Boeing Alert Requirements Bulletin 

B787–81205–SB270053–00 RB, Issue 

002, dated May 6, 2021, specifies prior 

or concurrent accomplishment of 

Boeing Alert Service Bulletin B787– 

81205–SB270044–00, Issue 003, dated 


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July 7, 2020; or Boeing Service Bulletin 

B787–81205–SB270046–00, Issue 002, 

dated October 24, 2019; as applicable, 

which specify procedures for installing 

FCE software update CBP 5.0. 

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. 

Costs of Compliance 

The FAA estimates that this AD 

affects 214 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 

Revising the AFM (retained actions from AD 

2020–24–04).

1 work-hour × $85 per hour = $85 ................. $0 $85 $18,190 

Updating the software ..................................... Up to 4 work-hours × $85 per hour = $340 ... (*) * 340 * 72,760 

* The table does not include the parts cost for the software. 

The FAA has determined that 

updating the software requires installing 

up to 8 software loads, at $300 per load, 

per operator. For the parts cost, the FAA 

has determined that a per-operator 

estimate is more accurate than a perairplane estimate. Therefore, the FAA 

estimates the total cost for software to be 

$2,400 per operator. 

The FAA has included all known 

costs in its cost estimate. According to 

the manufacturer, however, some 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: 

■ a. Removing Airworthiness Directive 

(AD) 2020–24–04, Amendment 39– 

21334 (85 FR 77991, December 3, 2020; 

corrected December 14, 2020 (85 FR 

80589)); and 

■ b. Adding the following new AD: 

2023–19–09 The Boeing Company: 

Amendment 39–22559; Docket No. 

FAA–2022–0674; Project Identifier AD– 

2021–00373–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 6, 2023. 

(b) Affected ADs 

This AD replaces AD 2020–24–04, 

Amendment 39–21334 (85 FR 77991, 

December 3, 2020; corrected December 14, 

2020 (85 FR 80589)) (AD 2020–24–04). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 787–8, 787–9, and 787–10 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 22, Auto flight. 

(e) Unsafe Condition 

This AD was prompted by reports 

indicating that the autopilot flight director 

system (AFDS) failed to transition to the 

instrument landing system localizer (LOC) 

beam after the consistent localizer capture 

function in the flight control modules 

initiated a transition to capture LOC during 

approach. The FAA is issuing this AD to 

address the AFDS failing to transition, which 

could result in localizer overshoot leading to 

glideslope descent on the wrong heading. 

Combined with a lack of flight deck effects 

for a consistent localizer capture mode 

failure, this condition could result in a 

controlled flight into terrain (CFIT). This AD 

was further prompted by reports of 

misleading vertical flight director guidance 

that in certain scenarios can be presented to 

the flightcrew during approach and could 

lead to CFIT or a runway overrun. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of the Existing 

Airplane Flight Manual (AFM), With New 

Terminating Action and Revised Affected 

Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2020–24–04, with new 

terminating action and revised affected 

airplanes. For airplanes on which Common 

Block Point (CBP) 5.1, 27 Flight Control 

Module (FCM) Operational Program Software 

(OPS) part number HNP5A–AL01–5041 or 

later approved software part number is not 

installed on FCM–L, FCM–C, and FCM–R: 

Within 14 days after December 18, 2020 (the 

effective date of AD 2020–24–04), revise the 

Operating Procedures chapter of the existing 

AFM and applicable corresponding 

operational procedures to incorporate the 

procedures specified in figure 1 to paragraph 

(g) of this AD. Revising the existing AFM to 

include the changes specified in paragraph 

(g) of this AD may be done by inserting a 


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copy of figure 1 to paragraph (g) of this AD 

into the existing AFM. Installing the software 

required by paragraph (h) of this AD 

terminates the requirement for revising the 

existing AFM in this paragraph. 

(h) New Required Actions 

For airplanes identified in paragraph A, 

‘‘Effectivity,’’ of Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, Issue 

002, dated May 6, 2021: Except as specified 

by paragraph (j) of this AD, at the applicable 

times specified in the ‘‘Compliance’’ 

paragraph of Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, Issue 

002, dated May 6, 2021, do all applicable 

actions identified in, and in accordance with, 

the Accomplishment Instructions of Boeing 

Alert Requirements Bulletin B787–81205– 

SB270053–00 RB, Issue 002, dated May 6, 

2021. 

Note 1 to paragraph (h): Guidance for 

accomplishing the actions required by 

paragraph (h) of this AD can be found in 

Boeing Alert Service Bulletin B787–81205– 

SB270053–00, Issue 002, dated May 6, 2021, 

which is referred to in Boeing Alert 

Requirements Bulletin B787–81205– 

SB270053–00 RB, Issue 002, dated May 6, 

2021. 

(i) Concurrent Actions 

For airplanes identified as Group 1, 

Configuration 1, and as Group 2, 

Configuration 1, in paragraph A, 

‘‘Effectivity,’’ of Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, Issue 

002, dated May 6, 2021: Prior to or 

concurrently with accomplishing the actions 

required by paragraph (h) of this AD, do all 

applicable actions identified as ‘‘RC’’ 

(required for compliance) in, and in 

accordance with, the applicable service 

information identified in paragraphs (i)(1) 

and (2) of this AD. 

(1) Boeing Alert Service Bulletin B787– 

81205–SB270044–00, Issue 003, dated July 7, 

2020. 

(2) Boeing Service Bulletin B787–81205– 

SB270046–00, Issue 002, dated October 24, 

2019. 

(j) Exceptions to Requirements of Paragraph 

(h) of This AD 

(1) Where the Compliance Time columns 

of the tables in the ‘‘Compliance’’ paragraph 

of Boeing Alert Requirements Bulletin B787– 

81205–SB270053–00 RB, Issue 002, dated 

May 6, 2021, use the phrase ‘‘the Issue 001 

date of the Requirements Bulletin B787– 

81205–SB270053–00 RB,’’ this AD requires 

using ‘‘the effective date of this AD.’’ 

(2) For airplanes on which CBP 5.1, 27 

FCM OPS part number HNP5A–AL01–5041 

or later-approved software part number was 

installed on FCM–L, FCM–C, and FCM–R in 

production, the actions specified in 

paragraph (h) of this AD are not required. 

(k) Terminating Action for AFM Revision 

Installation of the software update 

specified in the Accomplishment 

Instructions of Boeing Alert Requirements 

Bulletin B787–81205–SB270053–00 RB, Issue 

002, dated May 6, 2021, or installation of 

CBP 5.1, 27 FCM OPS part number HNP5A– 

AL01–5041 or later-approved software part 

number on FCM–L, FCM–C, and FCM–R in 

production, terminates the AFM revision 

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

AFM revision may be removed, provided that 

this software update has been installed on all 

affected airplanes in an operator’s fleet. 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for the 

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

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Requirements Bulletin B787– 

81205–SB270053–00 RB, Issue 001, dated 

February 19, 2021. 

(2) This paragraph provides credit for the 

actions specified in paragraph (i)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin B787–81205– 

SB270044–00, Issue 001, dated December 18, 

2018; or Boeing Alert Service Bulletin B787– 

81205–SB270044–00, Issue 002, dated 

November 20, 2019. 

(3) This paragraph provides credit for the 

actions specified in paragraph (i)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Service Bulletin B787–81205–SB270046–00, 

Issue 001, dated November 30, 2018. 

(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 the certification office, 

send it to the attention of the person 

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

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@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 2020–24–04 

are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

this AD. 

(5) Except as specified by paragraph (j) of 

this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (m)(5)(i) and (ii) of this AD apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. If a step or substep is 

labeled ‘‘RC Exempt,’’ then the RC 

requirement is removed from that step or 

substep. An AMOC is required for any 

deviations to RC steps, including substeps 

and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition 

(n) Related Information 

(1) For more information about this AD, 

contact Doug Tsuji, Aviation Safety Engineer, 

FAA, 2200 South 216th St., Des Moines, WA 


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Figure 1 to paragraph (g) - Operating Instructions 

(Required by AD 2020-24-04) 

Autopilot Flight Director System - Operating Instructions: 

When conducting an approach with a localizer-based navigation aid, monitor localizer raw 

data and call out any significant deviations. If AFDS performance is not satisfactory, the flight 

crew must intervene. Perform an immediate go-around if the airplane has not intercepted the 

final approach course as shown by the localizer deviation. 
67640 Federal Register / Vol. 88, No. 189 / Monday, October 2, 2023 / Rules and Regulations 

98198; phone: 206–231–3548; email: 

Douglas.Tsjui@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(o) 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) Boeing Alert Service Bulletin B787– 

81205–SB270044–00, Issue 003, dated July 7, 

2020. 

(ii) Boeing Service Bulletin B787–81205– 

SB270046–00, Issue 002, dated October 24, 

2019. 

(iii) Boeing Alert Requirements Bulletin 

B787–81205–SB270053–00 RB, Issue 002, 

dated May 6, 2021. 

(3) For service information 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 service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

St., Des Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(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 September 27, 2023. 

Victor Wicklund, 

Deputy Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2023–21673 Filed 9–29–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1643; Project 

Identifier MCAI–2022–01649–A; Amendment 

39–22555; AD 2023–19–05] 

RIN 2120–AA64 

Airworthiness Directives; British 

Aerospace (Operations) Limited and 

British Aerospace Regional Aircraft 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2017–19– 

22 for all British Aerospace Regional 

Aircraft Jetstream Series 3101 and 

Jetstream Model 3201 airplanes. AD 

2017–19–22 required incorporating BAE 

Systems’ Corrosion Prevention and 

Control program into the Airworthiness 

Limitations Section (ALS) of the 

existing instructions for continued 

airworthiness (ICA) for your airplane, 

which added new and more restrictive 

inspections for corrosion that include 

inspecting the door hinges/supporting 

structure and attachment bolts for the 

main spar joint and engine support, and 

the rudder hinge location on the vertical 

stabilizer, and applicable corrective 

actions. Since the FAA issued AD 2017– 

19–22, the Civil Aviation Authority 

(CAA) of the United Kingdom (UK) 

superseded the mandatory continuing 

airworthiness information (MCAI) 

issued by the European Aviation Safety 

Agency (now European Union Aviation 

Safety Agency) (EASA) to correct an 

unsafe condition on these products. 

This AD requires revising the ALS of the 

existing ICA for your airplane. The FAA 

is issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective November 6, 

2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 6, 2023. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1643; 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 MCAI, any 

comments received, and other 

information. The address for Docket 

Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

Material Incorporated by Reference: 

• For service information identified 

in this final rule, contact BAE Systems 

(Operations) Ltd., Customer Information 

Department, Prestwick International 

Airport, Ayrshire, KA9 2RW, Scotland, 

United Kingdom; phone: +44 3300 

488727; fax: +44 1292 675704; email: 

RApublications@baesystems.com; 

website: baesystems.com/businesses/ 

regionalaircraft/. 

• 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. It is also available 

at regulations.gov under Docket No. 

FAA–2023–1643. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Westbury, NY 11590; phone: (816) 329– 

4059; email: doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2017–19–22, 

Amendment 39–19052 (82 FR 44502, 

September 25, 2017) (AD 2017–19–22). 

AD 2017–19–22 applied to all British 

Aerospace Regional Aircraft Jetstream 

Series 3101 and Jetstream Model 3201 

airplanes. AD 2017–19–22 required 

incorporating new revisions to the ALS 

of the existing ICA for your airplane to 

incorporate new and more restrictive 

inspections for corrosion, which include 

inspecting the door hinges/supporting 

structure and attachment bolts of the 

main spar joint and engine support, and 

the hinge location on the vertical 

stabilizer, and repair or replacement, as 

applicable. The FAA issued AD 2017– 

19–22 to address corrosion on the 

rudder upper hinge bracket and internal 

wing, areas of the passenger/crew door 

hinges and supporting structure, the 

main spar joint, and the engine support 

attachment bolts, which could lead to 

reduced structural integrity with 

consequent loss of control. 

The NPRM published in the Federal 

Register on July 27, 2023 (88 FR 48393). 

The NPRM was prompted by UK CAA 

AD G–2022–0021, dated December 21, 

2022 (referred to after this as the MCAI), 

issued by the UK CAA, which is the 

aviation authority for the UK. The MCAI 

states that reports were received of 

corrosion on the rudder tab hinges, 

fuselage skin beneath the marker beacon 

antenna external doubler, and fuselage 

skin beneath the static vent external 

doubler, resulting in the need for new 

and more restrictive inspection 

requirements. The MCAI requires 

accomplishing the actions specified in 

BAE Systems Jetstream Series 3100 & 

3200 Corrosion Prevention and Control 

Programme, Manual Ref: JS/CPCP/01, 

Revision 9, dated April 15, 2022 (BAE 

Systems CPCP Manual JS/CPCP/01, 

Revision 9) within the associated 

threshold and intervals specified in BAE 

Systems CPCP Manual JS/CPCP/01, 

Revision 9. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1643. 

In the NPRM, the FAA proposed to 

require revising the ALS of the existing 


lotter on DSK11XQN23PROD with RULES1