39738 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 

2022–13–13 Airbus SAS: Amendment 39– 

22099; Docket No. FAA–2022–0382; 

Project Identifier MCAI–2021–01452–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus SAS Model 

A350–941 and –1041 airplanes, certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by reports that 

passenger door stop screws were found with 

missing screw heads. The FAA is issuing this 

AD to address the missing door stop screw 

heads, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Requirements 

Except as specified in paragraph (h) of this 

AD: Comply with all required actions and 

compliance times specified in, and in 

accordance with, European Union Aviation 

Safety Agency (EASA) AD 2021–0291, dated 

December 22, 2021 (EASA AD 2021–0291). 

(h) Exceptions to EASA AD 2021–0291 

(1) Where EASA AD 2021–0291 refers to its 

effective date, this AD requires using the 

effective date of this AD. 

(2) The ‘‘Remarks’’ section of EASA AD 

2021–0291 does not apply to this AD. 

(3) Paragraph (4) of EASA AD 2021–0291 

specifies to report results of the initial 

inspection to Airbus within a certain 

compliance time. For this AD, report 

inspection results of the initial inspection at 

the applicable time specified in paragraph 

(h)(3)(i) or (ii) of this AD. 

(i) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the end of the 

maintenance visit/check during which the 

inspection was performed. 

(ii) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the end of the 

maintenance visit/check during which the 

inspection was performed or within 30 days 

after the effective date of this AD, whichever 

occurs later. 

(4) Where Note 2 of paragraph (2) of EASA 

AD 2021–0291 specifies using ‘‘the 

instructions from an applicable Airbus 

Repair Design Approval Form (RDAF)’’ is 

acceptable for compliance with the corrective 

actions, this AD requires using corrective 

actions approved using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(5) Where paragraph (2) of EASA AD 2021– 

0291 refers to passenger door stop screws 

that are ‘‘damaged, as defined in the SB’’ this 

AD defines damage as broken passenger door 

stop screws. 

(6) Where service information referenced 

in EASA AD 2021–0291 specifies ‘‘a general 

visual inspection of the adjacent door stop 

area and surrounding structure (no lining 

removal required),’’ for this AD do a general 

visual inspection for any damage (e.g., 

broken passenger door stop screws), and 

repair any damage before further flight using 

a method approved by the Manager, Large 

Aircraft Section, International Validation 

Branch, FAA; or EASA; or Airbus SAS’s 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(i) Return of Parts 

Although the service information 

referenced in EASA AD 2021–0291 specifies 

to send broken screws to Airbus, this AD 

does not include that requirement. 

(j) Special Flight Permit 

Special flight permits may be issued in 

accordance with 14 CFR 21.197 and 21.199 

to operate the airplane to a location where 

the actions of this AD can be performed (if 

the operator elects to do so), provided no 

passengers are onboard. 

(k) Additional AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Large Aircraft 

Section, 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 responsible Flight 

Standards Office, as appropriate. If sending 

information directly to the Large Aircraft 

Section, International Validation Branch, 

send it to the attention of the person 

identified in paragraph (l) of this AD. 

Information may be emailed to: 9-AVS-AIR730-AMOC@faa.gov. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the responsible 

Flight Standards Office. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, Large Aircraft Section, 

International Validation Branch, FAA; or 

EASA; or Airbus SAS’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (k)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(l) Related Information 

For more information about this AD, 

contact Dan Rodina, Aerospace Engineer, 

Large Aircraft Section, International 

Validation Branch, FAA, 2200 South 216th 

Street, Des Moines, WA 98198; telephone 

and fax 206–231–3225; email dan.rodina@

faa.gov. 

(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 this AD specifies otherwise. 

(i) European Union Aviation Safety Agency 

(EASA) AD 2021–0291, dated December 22, 

2021. 

(ii) [Reserved] 

(3) For EASA AD 2021–0291, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 8999 

000; email ADs@easa.europa.eu; internet 

www.easa.europa.eu. You may find this 

material on the EASA website at https://

ad.easa.europa.eu. 

(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 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: https://

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

Issued on June 15, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–14195 Filed 7–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2021–0511; Project 

Identifier AD–2020–01229–E; Amendment 

39–22101; AD 2022–13–15] 

RIN 2120–AA64 

Airworthiness Directives; Williams 

International Co., L.L.C. Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


lotter on DSK11XQN23PROD with RULES1
Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 39739 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Williams International Co., L.L.C. 

(Williams) FJ44–2A, FJ44–2C, FJ44–3A, 

and FJ44–3A–24 model turbofan 

engines. This AD was prompted by a 

report of cracks in the high-pressure 

turbine (HPT) disk posts and failure of 

an HPT disk post, resulting in the 

contained fracture of an HPT disk post 

and blade. This AD requires removing 

the HPT disk, part number (P/N) 67093, 

from service before reaching defined 

cycle limits and replacing it with a part 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective August 9, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 9, 2022. 

ADDRESSES: For service information 

identified in this final rule, contact 

Williams International, Product 

Support, 2000 Centerpoint Parkway, 

Pontiac, MI 48341; phone: (800) 859– 

3544; website: http://www.williamsint.com/product-support. You may view 

this service information at the 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. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2021–0511; 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. 

FOR FURTHER INFORMATION CONTACT: Kyle 

Bush, Aviation Safety Engineer, Chicago 

ACO, FAA, 2300 East Devon Avenue, 

Des Plaines, IL 60018; phone: (847) 294– 

7870; email: kyle.bush@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD that would apply to certain 

Williams FJ44–2A, FJ44–2C, FJ44–3A, 

and FJ44–3A–24 model turbofan 

engines. The SNPRM published in the 

Federal Register on April 14, 2022 (87 

FR 22153). The SNPRM was prompted 

by a report of cracks in the HPT disk 

posts and failure of an HPT disk post, 

resulting in the contained fracture of an 

HPT disk post and blade. Subsequently, 

Williams notified the FAA that revised 

service information was available, 

which added additional serialnumbered FJ44–2A, FJ44–2C, and FJ44– 

3A model turbofan engines to the 

effectivity and updated the compliance 

time for replacing the HPT disk. In the 

SNPRM, the FAA proposed to require 

removing the HPT disk, P/N 67093, 

from service before reaching defined 

cycle limits and replacing it with a part 

eligible for installation. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received no comments on 

the SNPRM or on the determination of 

the costs. 

Conclusion 

The FAA reviewed the relevant data 

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. This AD is adopted as 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Williams 

International Service Bulletin (SB) 

WISB–72–1032, Revision 2, dated June 

4, 2020. This SB specifies procedures 

for removing and replacing the HPT 

rotor assemblies that include HPT disk, 

P/N 67093. This SB also provides 

instructions for incorporating the latest 

HPT combustor/fuel slinger module on 

FJ44–2A and FJ44–2C model turbofan 

engines. 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. 

Other Related Service Information 

The FAA reviewed Williams 

International SB WISB–72–1034, 

Revision 3, dated July 2, 2021. This SB 

describes procedures for re-identifying 

the HPT rotor assembly and HPT disk. 

Costs of Compliance 

The FAA estimates that this AD 

affects 242 engines installed on 

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 

Remove and replace the HPT disk ................ 33 work-hours × $85 per hour = $2,805 ........ $16,694 $19,499 $4,718,758 

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. 


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39740 Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 

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: 

2022–13–15 Williams International Co., 

L.L.C.: Amendment 39–22101; Docket 

No. FAA–2021–0511; Project Identifier 

AD–2020–01229–E. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective August 9, 2022. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Williams International 

Co., L.L.C. (Williams) FJ44–2A, FJ44–2C, 

FJ44–3A, and FJ44–3A–24 model turbofan 

engines with an engine serial number 

identified in paragraph 1.A., Effectivity, of 

Williams International Service Bulletin 

WISB–72–1032, Revision 2, dated June 4, 

2020 (the SB), with an installed highpressure turbine (HPT) disk, part number (P/ 

N) 67093. 

(d) Subject 

Joint Aircraft System Component (JASC) 

Code 7250, Turbine Section. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks in the HPT disk posts and failure of 

an HPT disk post, resulting in the contained 

fracture of an HPT disk post and blade. The 

FAA is issuing this AD to prevent cracking 

and failure of the HPT disk posts. The unsafe 

condition, if not addressed, could result in 

release of the HPT blade, damage to the 

engine, and damage to the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Required Actions 

(1) For FJ44–2A and FJ44–2C model 

turbofan engines, within the compliance 

times specified in Table 1 to Paragraph (g) of 

this AD, remove the affected HPT disk from 

service and replace it with a part eligible for 

installation using paragraphs 2.C. and E., 

Accomplishment Instructions—FJ44–2A & 

FJ44–2C, of the SB. 

(2) For FJ44–3A and FJ44–3A–24 model 

turbofan engines, within the compliance 

times specified in Table 1 to Paragraph (g) of 

this AD, remove the affected HPT disk from 

service and replace it with a part eligible for 

installation using paragraphs 3.C. and D., of 

the SB. 

(h) Installation Prohibition 

After the effective date of this AD, do not 

install onto any engine an HPT disk with P/ 

N 67093. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Chicago ACO, 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 certification office, 

send it to the attention of the person 

identified in paragraph (j) of this AD. 

(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) Related Information 

For more information about this AD, 

contact Kyle Bush, Aviation Safety Engineer, 

Chicago ACO, FAA, 2300 East Devon 

Avenue, Des Plaines, IL 60018; phone: (847) 

294–7870; email: kyle.bush@faa.gov. 

(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 service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Williams International Service Bulletin 

WISB–72–1032, Revision 2, dated June 4, 

2020. 

(ii) [Reserved] 

(3) For service information identified in 

this AD, contact Williams International, 

Product Support, 2000 Centerpoint Parkway, 

Pontiac, MI 48341; phone: (800) 859–3544; 

website: http://www.williams-int.com/ 

product-support. 

(4) You may view this service information 

at FAA, Airworthiness Products Section, 

Operational Safety Branch, FAA, 1200 

District Avenue, Burlington, MA 01803. For 


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Table 1 to Paragraph (g) - Compliance Time 

HPT disk, PIN 67093, cycles 

since new (CSN) as of the 

effective date of this AD 

0 to 999 CSN 

1,000 to 1,999 CSN 

2,000 to 2,999 CSN 

3,000 or higher CSN 

Replace within HPT disk 

cycles after the effective date 

of this AD 

620 

530 

245 

130 
Federal Register / Vol. 87, No. 127 / Tuesday, July 5, 2022 / Rules and Regulations 39741 

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: 

https://www.archives.gov/federal-register/cfr/ 

ibr-locations.html. 

Issued on June 17, 2022. 

Christina Underwood, 

Acting Director, Compliance & Airworthiness 

Division, Aircraft Certification Service. 

[FR Doc. 2022–14183 Filed 7–1–22; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2022–0464; Project 

Identifier MCAI–2021–01290–T; Amendment 

39–22097; AD 2022–13–11] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Airbus SAS Model A350–941 and –1041 

airplanes. This AD was prompted by a 

report of inadvertent auto flight system 

(AFS) altitude changes on the flight 

control unit (FCU). This AD requires 

revising the existing airplane flight 

manual (AFM) to include a procedure 

on the use of the AFS control panel ALT 

knob and replacing any affected FCU 

with a serviceable FCU, as specified in 

a European Union Aviation Safety 

Agency (EASA) AD, which is 

incorporated by reference. This AD also 

prohibits the installation of affected 

parts. The FAA is issuing this AD to 

address the unsafe condition on these 

products. 

DATES: This AD is effective August 9, 

2022. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of August 9, 2022. 

ADDRESSES: For material incorporated 

by reference (IBR) in this AD, contact 

EASA, Konrad-Adenauer-Ufer 3, 50668 

Cologne, Germany; telephone +49 221 

8999 000; email ADs@easa.europa.eu; 

internet www.easa.europa.eu. You may 

find this IBR material on the EASA 

website at https://ad.easa.europa.eu. 

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 in the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0464. 

Examining the AD Docket 

You may examine the AD docket at 

https://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2022–0464; 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 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. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, Large 

Aircraft Section, International 

Validation Branch, FAA, 2200 South 

216th St., Des Moines, WA 98198; 

telephone and fax 206–231–3225; email 

dan.rodina@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

EASA, which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2021–0260, 

dated November 18, 2021 (EASA AD 

2021–0260) (also referred to as the 

MCAI), to correct an unsafe condition 

for all Airbus SAS Model A350–941 and 

–1041 airplanes. 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all Airbus SAS Model A350– 

941 and –1041 airplanes. The NPRM 

published in the Federal Register on 

April 18, 2022 (87 FR 22816). The 

NPRM was prompted by a report of 

inadvertent AFS altitude changes on the 

FCU. The NPRM proposed to require 

revising the existing AFM to include a 

procedure on the use of the AFS control 

panel ALT knob and replacing any 

affected FCU with a serviceable FCU, as 

specified in EASA AD 2021–0260. The 

NPRM also proposed to prohibit the 

installation of affected parts. 

The FAA is issuing this AD to address 

erroneous target altitude during descent, 

climb, or go-around, which could result 

in an unexpected vertical trajectory 

deviation and loss of correct situational 

awareness that could potentially result 

in uncontrolled impact with the ground. 

See the MCAI for additional background 

information. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received a comment from 

the Air Line Pilots Association, 

International (ALPA) who supported the 

NPRM without change. 

Conclusion 

The FAA reviewed the relevant data, 

considered the comment received, and 

determined that air safety requires 

adopting this AD as proposed. Except 

for minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Accordingly, the FAA is issuing this AD 

to address the unsafe condition on these 

products. 

Related Service Information Under 1 

CFR part 51 

EASA AD 2021–0260 describes 

procedures for revising the existing 

AFM to include a procedure on the use 

of the AFS control panel ALT knob and 

replacing any affected FCU having part 

numbers (P/N) C31006AC01 or 

C31006AB01 with a serviceable FCU 

having P/N C31006AD01. 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 27 airplanes of U.S. registry. The 

FAA estimates the following costs to 

comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Up to 6 work-hours × $85 per hour = $510 ..................................................................... $27,000 Up to $27,510 ..... Up to $742,770. 


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