Federal Register / Vol. 72, No. 4 / Monday, January 8, 2007 / Proposed Rules 669 

Note 1: For the Model 369D, 369E, 369F, 

369FF, and 500N helicopters, the Handbook 

of Maintenance Instruction, Servicing and 

Maintenance, HMI, CSP–HMI–2, Chapter 32, 

Section 32–10–00, ‘‘Landing Gear Strut 

Inspection’’ pertains to the subject of this AD. 

Note 2: For the Model 369(A) (OH–6A), 

369H, 369HE, 369HS, and 369HM 

helicopters, the Basic Handbook of 

Maintenance Instructions CSP–H–2, Section 

6, ‘‘Landing Gear’’ pertains to the subject of 

this AD. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Los Angeles Aircraft 

Certification Office, Transport Airplane 

Directorate, FAA, for information about 

previously approved alternative methods of 

compliance. 

Issued in Fort Worth, Texas, on December 

26, 2006. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–41 Filed 1–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26771; Directorate 

Identifier 2005–SW–07–AD] 

RIN 2120–AA64 

Airworthiness Directives; Enstrom 

Helicopter Corporation Model F–28A, 

F–28C, F–28F, TH–28, 280, 280C, 280F, 

280FX, 480, and 480B Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: This document proposes 

adopting a new airworthiness directive 

(AD) for Enstrom Helicopter 

Corporation (Enstrom) Model F–28A, F–

28C, F–28F, TH–28, 280, 280C, 280F, 

280FX, 480, and 480B helicopters. The 

AD would require determining the 

installation dates for each main rotor 

push-pull control rod (push-pull rod), 

inspecting the push-pull rods for 

corrosion, replacing any push-pull rod 

which has corrosion that is severe 

enough to cause pitting, or has visible 

moisture inside the rod, and repairing 

each push-pull rod that has corrosion 

but no pitting. This proposal is 

prompted by one reported incident in 

which the helicopter pilot encountered 

severe in flight vibration due to the 

failure of a push-pull rod, requiring an 

emergency landing. The actions 

specified by the proposed AD are 

intended to detect corrosion and 

prevent failure of a push-pull rod, and 

subsequent loss of control of the 

helicopter. 

DATES: Comments must be received on 

or before March 9, 2007. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically; 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically; 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590; 

• Fax: 202–493–2251; or 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

You may get the service information 

identified in this proposed AD from The 

Enstrom Helicopter Corporation, Twin 

County Airport, P.O. Box 490, 

Menominee, Michigan 49858. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http://dms.dot.gov. 

FOR FURTHER INFORMATION CONTACT: 

Shawn Malekpour, Aviation Safety 

Engineer, FAA, Chicago Aircraft 

Certification Office, 2300 East Devon 

Ave., Des Plaines, Illinois 60018, 

telephone (847) 294–7837, fax (847) 

294–7834. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to submit any written 

data, views, or arguments regarding this 

proposed AD. Send your comments to 

the address listed under the caption 

ADDRESSES. Include the docket number 

‘‘FAA–2006–26771, Directorate 

Identifier 2005–SW–07–AD’’ at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the proposed AD. We will consider all 

comments received by the closing date 

and may amend the proposed AD in 

light of those comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of our docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Management 

System (DMS) Docket Office between 

9 a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The 

Docket Office (telephone 1–800–647–

5227) is located at the plaza level of the 

Department of Transportation NASSIF 

Building in Room PL–401 at 400 

Seventh Street, SW., Washington, DC. 

Comments will be available in the AD 

docket shortly after the DMS receives 

them. 

Discussion 

This document proposes adopting a 

new AD for Enstrom Model F–28A, F–

28C, F–28F, TH–28, 280, 280C, 280F, 

280FX, 480, and 480B helicopters. The 

proposed AD would require reviewing 

the helicopter maintenance records and 

determining the installation dates for 

the push-pull rods. If the dates cannot 

be determined from the maintenance 

records, using the ‘‘Date MFD’’, which 

is located on the helicopter data plate, 

would be used as the installation date 

for the push-pull rods. The proposed 

AD would also require a visual 

inspection for corrosion on the exterior 

and interior of the three push-pull rods, 

part number (P/N) 28–16253-all dash 

numbers (for Model F–28A, F–28C, F–

28F, 280, 280C, 280F, and 280FX 

helicopters) or P/N 4140532-all dash 

numbers (for Model TH–28, 480, and 

480B helicopters), using the compliance 

times stated in the following table. 

Replacing any push-pull rod that has 

corrosion that is severe enough to cause 

pitting or has moisture inside the rod, 

and repairing any push-pull rod that has 

corrosion but no pitting, would be 

required before further flight. Repairing 

a push-pull rod consists of cleaning the 

push-pull rod, applying a protective 

coating, and sealing the push-pull rod 

before reinstalling it on a helicopter. 


sroberts on PROD1PC70 with PROPOSALS
670 Federal Register / Vol. 72, No. 4 / Monday, January 8, 2007 / Proposed Rules 

Helicopter models Push-pull rod service life Compliance times 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for 20 or 

more years.

Inspect within 10 hours time-in-service (TIS) 

or at next annual inspection, whichever occurs first. 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for 10 or 

more years, but less than 20 years.

Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first. 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for less 

than 10 years.

Inspect before the service life of the push-pull 

rod reaches 10 years since initial installation. 

Model TH–28, 480, and 480B helicopters ......... Push-pull rod that has been installed for 10 or 

more years.

Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first. 

Model TH–28, 480, and 480B helicopters ......... Push-pull rod that has been installed for less 

than 10 years.

Inspect before the service life of the push-pull 

rod reaches 10 years since initial installation. 

This proposal is prompted by one 

reported incident in which severe inflight vibrations required an emergency 

landing. Upon landing, the tail rotor, 

tail rotor gearbox, and horizontal 

stabilizer separated from the helicopter. 

A subsequent investigation revealed a 

rupture of the lower end of one of the 

three push-pull rods. The actions 

specified by the proposed AD are 

intended to detect corrosion on a pushpull rod and prevent failure of a pushpull rod, and subsequent loss of control 

of the helicopter. 

We have reviewed the following 

service information: 

• Enstrom Helicopter Corporation 

Service Directive Bulletin No. 0096, 

dated September 10, 2003, which 

describes visually inspecting the pushpull rods for corrosion and internal 

moisture, provides for repairing light 

corrosion, and is applicable to Model F–

28A, F–28C, F–28F, 280, 280C, 280F, 

and 280FX helicopters. 

• Enstrom Helicopter Corporation 

Service Directive Bulletin No. T–019, 

dated September 10, 2003, which 

describes visually inspecting the pushpull rods for corrosion and internal 

moisture, provides for repairing light 

corrosion, and is applicable to Model 

TH–28, 480, and 480B helicopters. 

• Enstrom Helicopter Corporation 

Service Information Letter (SIL) No. T–

019, dated December 9, 2003, applicable 

to Model TH–28, 480, and 480B 

helicopters, which describes visually 

inspecting each push-pull rod for a 

crack, nick, scratch, dent, corrosion, 

damaged threads, bending, and contact 

wear. We are not proposing to require 

the inspections specified in the SIL. 

• Enstrom Helicopter Corporation 

Service Information Letter No. 0156, 

dated December 9, 2005, applicable to 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters, which 

describes visually inspecting each pushpull rod for a crack, nick, scratch, dent, 

corrosion, damaged threads, bending, 

and contact wear. We are not proposing 

to require the inspections specified in 

the SIL. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type designs. Therefore, the 

proposed AD would require 

determining the installation date for the 

push-pull rods and inspecting each of 

the three push-pull rods for corrosion. If 

corrosion that is severe enough to cause 

pitting is found, or if moisture is visible 

on the inside of a push-pull rod, the AD 

would require replacing the push-pull 

rod. If there is corrosion without pitting 

on a push-pull rod, that push-pull rod 

may be repaired. Repairing a push-pull 

rod consists of cleaning the push-pull 

rod, applying a protective coating, and 

sealing the push-pull rod before 

remarking it and reinstalling it on a 

helicopter. The actions would be 

required to be accomplished in 

accordance with the specified portions 

of the Enstrom service directive 

bulletins described previously. 

We estimate that this proposed AD 

would affect 378 helicopters of U.S. 

registry, and that the required actions 

would take the following numbers of 

work hours to accomplish on each 

helicopter at an average labor rate of $80 

per work hour: 

• 8 work hours to remove, 

disassemble, and inspect the 3 pushpull rods; 

• 9 work hours to repair corrosion 

without pitting, remark each push-pull 

rod, and reassemble each push-pull rod; 

and 

• 3 work hours to reinstall 3 pushpull rods on the helicopter. Required 

parts would cost approximately $900 

per helicopter. Based on these figures, 

the total cost impact of the proposed AD 

on U.S. operators would be $945,000 

($2,500 per helicopter), assuming 3 

push-pull rods are replaced on each 

helicopter. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, 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 that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 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. 

We prepared a draft economic 

evaluation of the estimated costs to 

comply with this proposed AD. See the 

DMS to examine the draft economic 

evaluation. 

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. 

We are 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 


sroberts on PROD1PC70 with PROPOSALS
Federal Register / Vol. 72, No. 4 / Monday, January 8, 2007 / Proposed Rules 671 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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. Section 39.13 is amended by 

adding a new airworthiness directive to 

read as follows: 

Enstrom Helicopter Company: Docket No. 

FAA–2006–26771; Directorate Identifier 

2005–SW–07–AD. 

Applicability: Model F–28A, F–28C, and 

F–28F helicopters, excluding serial number 

(S/N) 816 and subsequent; Model 280, 280C, 

280F, and 280FX helicopters, excluding S/N 

2100 and subsequent; and Model TH–28, 

480, and 480B helicopters, excluding S/N 

5058 and subsequent, certificated in any 

category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To detect corrosion and prevent failure of 

a main rotor push-pull control rod (push-pull 

rod), and subsequent loss of control of the 

helicopter, accomplish the following: 

(a) Within 10 hours time-in-service (TIS) or 

at the next annual inspection, whichever 

occurs first, review the helicopter 

maintenance records and determine the date 

that each push-pull rod, part number (P/N) 

28–16253-all dash numbers (for Model F–

28A, F–28C, F–28F, 280, 280C, 280F, and 

280FX helicopters) and P/N 4140532-all dash 

numbers (for Model TH–28, 480, and 480B 

helicopters), was installed. If the date cannot 

be determined from the maintenance records, 

use the ‘‘Date MFD’’, which is located on the 

helicopter data plate, as the installation date 

for the push-pull rod. 

(b) For Model F–28A, F–28C, F–28F, 280, 

280C, 280F, and 280FX helicopters, using the 

compliance times stated in Table 1 of this 

AD, visually inspect the exterior and interior 

of each of the three push-pull rods for 

corrosion severe enough to cause pitting or 

any moisture, paying special attention to the 

area of the lower fitting, in accordance with 

section 5.1., INSPECTION, in Enstrom 

Helicopter Corporation Service Directive 

Bulletin No. 0096, dated September 10, 2003 

(SDB 0096). 

TABLE 1 

Helicopter models Push-pull rod service life Compliance times 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for 20 or 

more years.

Inspect within 10 hours time-in-service (TIS) 

or at next annual inspection, whichever occurs first. 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for 10 or 

more years, but less than 20 years.

Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first. 

Model F–28A, F–28C, F–28F, 280, 280C, 

280F, and 280FX helicopters.

Push-pull rod that has been installed for less 

than 10 years.

Inspect before the service life of the push-pull 

rod reaches 10 years since initial installation. 

(1) Before further flight, if corrosion 

without pitting is found on a push-pull rod, 

then repair, reassemble, remark, and reinstall 

it in accordance with section 5.2., REPAIR/ 

REASSEMBLY, in SDB 0096. 

(2) Before further flight, if corrosion is 

found that is severe enough to cause pitting, 

or if any moisture is visible on the inside of 

a push-pull rod, replace it with an airworthy 

push-pull rod. 

Note 1: Determining continued 

serviceability of the push-pull rods by 

inspecting the exterior only of each push-pull 

rod is described in Enstrom Helicopter 

Corporation Service Information Letter No. 

0156, dated December 9, 2003. 

(c) For Model TH–28, 480 and 480B 

helicopters, using the compliance times 

stated in Table 2 of this AD, visually inspect 

the exterior and interior of each of the three 

push-pull rods for corrosion severe enough to 

cause pitting or any moisture, paying special 

attention to the area of the lower fitting, in 

accordance with section 5.1., INSPECTION, 

in Enstrom Helicopter Corporation Service 

Directive Bulletin No. T–019, dated 

September 10, 2003 (SDB T–019). 

TABLE 2 

Helicopter models Push-pull rod service life Compliance times 

Model TH–28, 480, and 480B helicopters ......... Push-pull rod that has been installed for 10 or 

more years.

Inspect within 50 hours TIS or at the next annual inspection, whichever occurs first. 

Model TH–28, 480, and 480B helicopters ......... Push-pull rod that has been installed for less 

than 10 years.

Inspect before the service life of the push-pull 

rod reaches 10 years since initial installation. 


sroberts on PROD1PC70 with PROPOSALS
672 Federal Register / Vol. 72, No. 4 / Monday, January 8, 2007 / Proposed Rules 

(1) Before further flight, if corrosion 

without pitting is found on a push-pull rod, 

then repair, reassemble, remark, and reinstall 

it in accordance with section 5.2., REPAIR/ 

REASSEMBLY, in SDB T–019. 

(2) Before further flight, if corrosion is 

found that is severe enough to cause pitting, 

or if any moisture is visible on the inside of 

a push-pull rod, replace it with an airworthy 

push-pull rod. 

Note 2: Determining continued 

serviceability of the push-pull rods by 

inspecting the exterior only of each push-pull 

rod is described in Enstrom Helicopter 

Corporation Service Information Letter No. 

T–019, dated December 9, 2003. 

(d) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact Chicago Aircraft Certification 

Office, Small Airplane Directorate, FAA, for 

information about previously approved 

alternative methods of compliance. 

Issued in Fort Worth, Texas, on December 

26, 2006. 

David A. Downey, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. E7–43 Filed 1–5–07; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–26693; Directorate 

Identifier 2006–CE–90–AD] 

RIN 2120–AA64 

Airworthiness Directives; Reims 

Aviation S.A. F406 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

This AD is issued following a nose landing 

gear collapse during takeoff roll. Several 

expertises proved that the locking device of 

the Nose Landing Gear (NLG) actuator rod 

was on several F406 airplanes not 

conforming with the installation approved by 

the manufacturer. 

There were two different landing gear 

actuator designs installed on the F406 

airplanes. The actuators used different 

locking devices to retain the spherical 

rod-end to the actuator rod. Use of the 

incorrect locking device could allow the 

spherical rod-end to disconnect from 

the actuator rod. The proposed AD 

would require actions that are intended 

to address the unsafe condition 

described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by February 7, 2007. 

ADDRESSES: You may send comments by 

any of the following methods: 

• DOT Docket Web site: Go to http:// 

dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Fax: (202) 493–2251. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://dms.dot.gov; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

proposed AD, the regulatory evaluation, 

any comments received, and other 

information. The street address for the 

Docket Office (telephone (800) 647–

5227) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone (816) 329–4144; fax (816) 

329–4090. 

SUPPLEMENTARY INFORMATION: 

Streamlined Issuance of AD 

The FAA is implementing a new 

process for streamlining the issuance of 

ADs related to MCAI. The streamlined 

process will allow us to adopt MCAI 

safety requirements in a more efficient 

manner and will reduce safety risks to 

the public. This process continues to 

follow all FAA AD issuance processes to 

meet legal, economic, Administrative 

Procedure Act, and Federal Register 

requirements. We also continue to meet 

our technical decision-making 

responsibilities to identify and correct 

unsafe conditions on U.S.-certificated 

products. 

This proposed AD references the 

MCAI and related service information 

that we considered in forming the 

engineering basis to correct the unsafe 

condition. The proposed AD contains 

text copied from the MCAI and for this 

reason might not follow our plain 

language principles. 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2006–26693; Directorate Identifier 

2006–CE–90–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The Direction Ge ́ne ́rale de L’Aviation 

Civile (DGAC), which is the aviation 

authority for France, has issued AD No. 

F–2005–065, dated April 27, 2005 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

This AD is issued following a nose landing 

gear collapse during takeoff roll. Several 

expertises proved that the locking device of 

the Nose Landing Gear (NLG) actuator rod 

was on several F406 airplanes not 

conforming with the installation approved by 

the manufacturer. 

As Main Landing Gear (MLG) actuator rod 

locking devices are similar to the NLG ones, 

then MLG actuator locking devices shall also 

be inspected. 

This AD requires inspection of the NLG 

and MLG locking devices and as requested 

their replacement to comply with the 

manufacturer’s approved design. 

There were two different landing gear 

actuator designs installed on the F406 

airplanes. The actuators used different 

locking devices to retain the spherical 

rod-end to the actuator rod. Use of the 

incorrect locking device could allow the 

spherical rod-end to disconnect from 

the actuator rod and consequently the 

landing gear could collapse. This AD 

requires you to do a one time inspection 

of the landing gear actuators and, if an 

incorrect locking device is found, 

replace it with the correct locking 

device. 


sroberts on PROD1PC70 with PROPOSALS