Federal Register / Vol. 71, No. 116 / Friday, June 16, 2006 / Rules and Regulations 34801 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

(3) AMOCs approved previously according 

to AD 98–20–01, are approved as AMOCs for 

the corresponding provisions of this AD. 

Related Information 

(m) Canadian airworthiness directive CF–

1998–14R4, dated June 1, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

listed in Table 1 of this AD, as applicable, to 

perform the actions that are required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centre-ville, 

Montreal, Quebec H3C 3G9, Canada, for a 

copy of this service information. You may 

review copies at the Docket Management 

Facility, U.S. Department of Transportation, 

400 Seventh Street, SW., room PL–401, 

Nassif Building, Washington, DC; on the 

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

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at the NARA, 

call (202) 741–6030, or go to http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 1.—MATERIAL INCORPORATED BY REFERENCE

Service information Revision level Date 

Bombardier Service Bulletin 601R–11–080 .................................................................. A .................................................. October 11, 2005. 

Bombardier Service Bulletin 601R–27–111 .................................................................. Original ........................................ March 6, 2000. 

Bombardier Service Bulletin 601R–27–114, excluding Appendix A ............................. C .................................................. November 9, 2004. 

Bombardier Service Bulletin 601R–27–115 .................................................................. E .................................................. October 7, 2004. 

Bombardier Service Bulletin 601R–27–116 .................................................................. C .................................................. August 26, 2004. 

Bombardier Service Bulletin 601R–34–128 .................................................................. C .................................................. March 28, 2005. 

Canadair Temporary Revision RJ/128 to the Canadair Regional Jet Airplane Flight 

Manual, CSP A–012.

Original ........................................ November 28, 2003. 

Issued in Renton, Washington, on June 5, 

2006. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 06–5326 Filed 6–15–06; 8:45 am] 

BILLING CODE 4910–13–U 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23173; Directorate 

Identifier 2005–NM–190–AD; Amendment 

39–14644; AD 2006–12–18] 

RIN 2120–AA64 

Airworthiness Directives; Short 

Brothers Model SD3 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Short Brothers Model SD3 airplanes. 

This AD requires installing additional 

fuel tank bonding jumpers, performing 

an in-place resistance check of the float 

switches, inspecting certain internal 

components of the fuel tanks, and 

performing related corrective actions if 

necessary. This AD also requires 

revisions to the Airworthiness 

Limitations section of the Instructions 

for Continued Airworthiness, and to the 

airplane flight manual procedures for 

operation during icing conditions and 

fuel system failures. This AD results 

from fuel system reviews conducted by 

the manufacturer. We are issuing this 

AD to prevent ignition sources inside 

the fuel tanks, which could lead to fire 

or explosion. 

DATES: This AD becomes effective July 

21, 2006. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 21, 2006. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

dms.dot.gov or in person at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street 

SW., Nassif Building, Room PL–401, 

Washington, DC. 

Contact Short Brothers, Airworthiness 

& Engineering Quality, P.O. Box 241, 

Airport Road, Belfast BT3 9DZ, 

Northern Ireland, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98055–4056; telephone 

(425) 227–2125; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may examine the airworthiness 

directive (AD) docket on the Internet at 

http://dms.dot.gov or in person at the 

Docket Management Facility office 

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

through Friday, except Federal holidays. 

The Docket Management Facility office 

(telephone (800) 647–5227) is located on 

the plaza level of the Nassif Building at 

the street address stated in the 

ADDRESSES section. 

Discussion 

The FAA issued a supplemental 

notice of proposed rulemaking (NPRM) 

to amend 14 CFR part 39 to include an 

AD that would apply to all Short 

Brothers Model SD3 airplanes. That 

supplemental NPRM was published in 

the Federal Register on April 12, 2006 

(71 FR 18686). That supplemental 

NPRM proposed to require installing 

additional fuel tank bonding jumpers, 

performing an in-place resistance check 

of the float switches, inspecting certain 

internal components of the fuel tanks, 

and performing related corrective 

actions if necessary. That supplemental 

NPRM also proposed to require 

revisions to the Airworthiness 

Limitations section of the Instructions 

for Continued Airworthiness, and to the 

airplane flight manual (AFM) 

procedures for operation during icing 

conditions and fuel system failures. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the supplemental NPRM 

or on the determination of the cost to 

the public. 

Clarification of Service Information 

We have revised the reference to the 

advance amendment bulletin specified 

in paragraph (f) of this AD. Rather than 

one bulletin, there are four bulletins, 

each applicable to a certain model 

airplane. The information in each 


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bulletin revises the applicable AFM for 

that model airplane. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD with the change 

previously discussed. We have 

determined that this change will neither 

increase the economic burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD affects about 54 airplanes of 

U.S. registry. The average labor rate is 

estimated to be $80 per work hour. 

The required revisions to the AFM 

and airplane maintenance manual 

(AMM) will take about 1 work hour per 

airplane. Based on these figures, the 

estimated cost of the required revisions 

for U.S. operators is $4,320, or $80 per 

airplane. 

The required resistance check, 

inspections, and jumper installations, 

will take about 40 work hours per 

airplane. Required parts will cost about 

$10 per airplane. Based on these figures, 

the estimated cost of these required 

actions for U.S. operators is $173,340, or 

$3,210 per airplane. 

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. 

Regulatory Findings 

We have determined that 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) Is not a ‘‘significant rule’’ under 

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 regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by adding the following new 

airworthiness directive (AD): 

2006–12–18 Short Brothers PLC: 

Amendment 39–14644. Docket No. 

FAA–2005–23173; Directorate Identifier 

2005–NM–190–AD. 

Effective Date 

(a) This AD becomes effective July 21, 

2006. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Shorts Model 

SD3–60 SHERPA, SD3-SHERPA, SD3–30, 

and SD3–60 airplanes, certificated in any 

category. 

Note 1: This AD requires revisions to 

certain operator maintenance documents to 

include new inspections. Compliance with 

these inspections is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired in 

the areas addressed by these inspections, the 

operator may not be able to accomplish the 

inspections described in the revisions. In this 

situation, to comply with 14 CFR 91.403(c), 

the operator must request approval for an 

alternative method of compliance according 

to paragraph (i) of this AD. The request 

should include a description of changes to 

the required inspections that will ensure the 

continued damage tolerance of the affected 

structure. The FAA has provided guidance 

for this determination in Advisory Circular 

(AC) 25–1529. 

Unsafe Condition 

(d) This AD results from fuel system 

reviews conducted by the manufacturer. We 

are issuing this AD to prevent ignition 

sources inside the fuel tanks, which could 

lead to fire or explosion. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Revision of Airplane Flight Manual (AFM) 

(f) Within 30 days after the effective date 

of this AD, revise the Limitations and Normal 

Procedures sections of the AFMs as specified 

in Table 1 of this AD to include the 

information in the applicable Shorts advance 

amendment bulletins as specified in Table 1 

of this AD. The advance amendment 

bulletins address operation during icing 

conditions and fuel system failures. 

Thereafter, operate the airplane according to 

the limitations and procedures in the 

applicable advance amendment bulletin. 

Note 2: The requirements of paragraph (f) 

of this AD may be done by inserting a copy 

of the applicable advance amendment 

bulletin into the AFM. When the applicable 

advance amendment bulletin has been 

included in general revisions of the AFM, the 

general revisions may be inserted into the 

AFM and the advance amendment bulletin 

may be removed, provided the relevant 

information in the general revision is 

identical to that in the advance amendment 

bulletin. 

TABLE 1.—AFM REVISIONS

Airplane model Shorts advance amendment bulletin To AFM 

SD3–30 .............................................................. 1/2004, dated July 13, 2004 ............................ SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, 

SBH.3.8, and SB.3.9. 

SD3–60 .............................................................. 1/2004, dated July 13, 2004 ............................ SB.4.3, SB.4.6, and SB.4.8. 

SD3–60 SHERPA .............................................. 1/2004, dated July 13, 2004 ............................ SB.5.2. 


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TABLE 1.—AFM REVISIONS—Continued 

Airplane model Shorts advance amendment bulletin To AFM 

SD3–SHERPA ................................................... 1/2004, dated July 13, 2004 ............................ SB.6.2. 

Revision of Airworthiness Limitation (AWL) 

Section 

(g) Within 180 days after the effective date 

of this AD: Revise the AWL section of the 

Instructions for Continued Airworthiness by 

incorporating airplane maintenance manual 

(AMM) sections 5–20–01 and 5–20–02 as 

introduced by the Shorts temporary revisions 

(TR) specified in Table 2 of this AD into the 

AWL section of the AMMs for the airplane 

models specified in Table 2. Thereafter, 

except as provided by paragraph (i) of this 

AD, no alternative structural inspection 

intervals may be approved for the 

longitudinal skin joints in the fuselage 

pressure shell. 

Note 3: The requirements of paragraph (g) 

of this AD may be done by inserting a copy 

of the applicable TR into the applicable 

AMM. When the TR has been included in 

general revisions of the AMM, the general 

revisions may be inserted in the AMM and 

the TR may be removed, provided the 

relevant information in the general revision 

is identical to that in the TR. 

TABLE 2.—AMM TEMPORARY REVISIONS

Airplane model Temporary revision Dated To AMM 

SD3–30 .......................................... TR330–AMM–13 ........................... June 21, 2004 ............................... SD3–30 AMM. 

SD3–30 .......................................... TR330–AMM–14 ........................... June 21, 2004 ............................... SD3–30 AMM. 

SD3–60 .......................................... TR360–AMM–33 ........................... July 27, 2004 ................................ SD3–60 AMM. 

SD3–60 .......................................... TR360–AMM–34 ........................... July 27, 2004 ................................ SD3–60 AMM. 

SD3–60 SHERPA .......................... TRSD360S–AMM–14 ................... July 29, 2004 ................................ SD3–60 SHERPA AMM. 

SD3–60 SHERPA .......................... TRSD360S–AMM–15 ................... July 29, 2004 ................................ SD3–60 SHERPA AMM. 

SD3–SHERPA ............................... TRSD3S–AMM–15 ....................... July 28, 2004 ................................ SD3 SHERPA AMM. 

SD3–SHERPA ............................... TRSD3S–AMM–16 ....................... July 28, 2004 ................................ SD3 SHERPA AMM. 

Resistance Check, Inspection, and Jumper 

Installation 

(h) Within 180 days after the effective date 

of this AD: Perform the insulation resistance 

check, general visual inspections, and 

bonding jumper wire installations; in 

accordance with Shorts Service Bulletin 

SD330–28–37, SD360–28–23, SD360 

SHERPA–28–3, or SD3 SHERPA–28–2; all 

dated June 2004; as applicable. If any defect 

or damage is discovered during any 

inspection or check required by this AD, 

before further flight, repair the defect or 

damage using a method approved by either 

the Manager, International Branch, ANM–

116, Transport Airplane Directorate, FAA; or 

the Civil Aviation Authority (CAA) (or its 

delegated agent). 

Note 4: For the purposes of this AD, a 

general visual inspection is: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made from within touching 

distance unless otherwise specified. A mirror 

may be necessary to ensure visual access to 

all surfaces in the inspection area. This level 

of inspection is made under normally 

available lighting conditions such as 

daylight, hangar lighting, flashlight, or 

droplight and may require removal or 

opening of access panels or doors. Stands, 

ladders, or platforms may be required to gain 

proximity to the area being checked.’’

Alternative Methods of Compliance 

(AMOCs) 

(i)(1) The Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, has the authority to approve AMOCs 

for this AD, if requested in accordance with 

the procedures found in 14 CFR 39.19. 

(2) Before using any AMOC approved in 

accordance with § 39.19 on any airplane to 

which the AMOC applies, notify the 

appropriate principal inspector in the FAA 

Flight Standards Certificate Holding District 

Office. 

Related Information 

(j) British airworthiness directive G–2004–

0021 R1, dated September 15, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(k) You must use the applicable service 

information specified in Table 3, Table 4, and 

Table 5 of this AD to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. (The document number 

of the advance amendment bulletins is listed 

only on page 1 of those documents.) The 

Director of the Federal Register approved the 

incorporation by reference of these 

documents in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. Contact Short 

Brothers, Airworthiness & Engineering 

Quality, P.O. Box 241, Airport Road, Belfast 

BT3 9DZ, Northern Ireland, for a copy of this 

service information. You may review copies 

at the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., Room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/ 

federal_register/code_of_federal_regulations/ 

ibr_locations.html. 

TABLE 3.—SHORTS TEMPORARY REVISIONS INCORPORATED BY REFERENCE

Temporary revision Dated 

To airplane 

maintenance 

manual 

TR330–AMM–13 ................................................................... June 21, 2004 ...................................................................... SD3–30. 

TR330–AMM–14 ................................................................... June 21, 2004 ...................................................................... SD3–30. 

TR360–AMM–33 ................................................................... July 27, 2004 ........................................................................ SD3–60. 

TR360–AMM–34 ................................................................... July 27, 2004 ........................................................................ SD3–60. 

TRSD360S–AMM–14 ........................................................... July 29, 2004 ........................................................................ SD3–60 SHERPA. 

TRSD360S–AMM–15 ........................................................... July 29, 2004 ........................................................................ SD3–60 SHERPA. 

TRSD3S–AMM–15 ............................................................... July 28, 2004 ........................................................................ SD3 SHERPA. 

TRSD3S–AMM–16 ............................................................... July 28, 2004 ........................................................................ SD3 SHERPA. 


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TABLE 4.—SHORTS ADVANCE AMENDMENT BULLETINS INCORPORATED BY REFERENCE

Advance amendment bulletin To airplane flight manual 

1/2004, dated July 13, 2004 ..................................................................... SBH.3.2, SBH.3.3, SBH.3.6, SBH.3.7, SBH.3.8, and SB.3.9. 

1/2004, dated July 13, 2004 ..................................................................... SB.4.3, SB.4.6, and SB.4.8. 

1/2004, dated July 13, 2004 ..................................................................... SB.5.2. 

1/2004, dated July 13, 2004 ..................................................................... SB.6.2. 

TABLE 5.—SHORTS SERVICE BULLETINS INCORPORATED BY REFERENCE

Service bulletin Dated 

SD330–28–37 ......................... June 2004. 

SD360–28–23 ......................... June 2004. 

SD360 SHERPA–28–3 ........... June 2004. 

SD3 SHERPA–28–2 ............... June 2004. 

Issued in Renton, Washington, on June 5, 

2006. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–5288 Filed 6–15–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–23334; Directorate 

Identifier 2005–CE–53–AD; Amendment 39–

14651; AD 2006–12–25] 

RIN 2120–AA64 

Airworthiness Directives; General 

Machine—Diecron, Inc. Actuator Nut 

Assembly for the Right Main Landing 

Gear Installed on Certain Raytheon 

Aircraft Company (Formerly Beech) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for General 

Machine—Diecron, Inc. (GMD) actuator 

nut assembly, part number (P/N) 

GMD115–810029–17 and P/N GMD115–

810029–23, that are installed on certain 

Raytheon Aircraft Company (Raytheon) 

(formerly Beech) airplanes that are not 

equipped with a hydraulic main landing 

gear (MLG) or modified to a hydraulic 

MLG. This AD requires you to 

determine by maintenance records 

check and/or inspection whether any 

actuator nut assembly, P/N GMD115–

810029–17 or P/N GMD115–810029–23, 

is installed on the right main MLG 

actuator, and, if installed, requires you 

to replace it with a new actuator nut 

assembly, P/N GMD115–810029–23B or 

FAA-approved equivalent P/N. This AD 

results from several reports of failures of 

the actuator nut assembly, P/N 

GMD115–810029–17 and P/N GMD115–

810029–23. We are issuing this AD to 

prevent failure of the actuator nut 

assembly for the right MLG actuator, 

which could result in failure of the 

MLG. This failure could prevent the 

extension or retraction of the MLG. 

DATES: This AD becomes effective on 

July 28, 2006. 

As of July 28, 2006, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact General Machine—Diecron, Inc., 

3131 U.S. Highway 41, Griffin, Georgia 

30224, telephone: (770) 228–6200; 

facsimile: (770) 228–6299. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–23334; Directorate Identifier 

2005–CE–53–AD. 

FOR FURTHER INFORMATION CONTACT: Don 

Buckley, Aerospace Engineer, Airframe 

and Propulsion Branch, ACE–117A, 

FAA, Atlanta Aircraft Certification 

Office, One Crown Center, 1895 Phoenix 

Boulevard, Suite 450, Atlanta, Georgia 

30337–2748, telephone: (770) 703–6086; 

facsimile: (770) 703–6097. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 30, 2006, we issued a 

proposal to amend part 39 of the Federal 

Aviation Regulations (14 CFR part 39) to 

include an AD that would apply to the 

GMD actuator nut assembly, P/N 

GMD115–810029–17 or P/N GMD115–

810029–23, that is installed on certain 

airplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on 

February 3, 2006 (71 FR 5796). The 

NPRM proposed to require you to 

determine by maintenance records 

check and/or inspection whether any 

actuator nut assembly, P/N GMD115–

810029–17 or P/N GMD115–810029–23, 

is installed on the right MLG actuator, 

and, if installed, would require you to 

replace it with a new actuator nut 

assembly, P/N GMD115–810029–23B or 

FAA-approved equivalent P/N. 

Comments 

We provided the public the 

opportunity to participate in developing 

this AD. The following presents the 

comments received on the proposal and 

FAA’s response to each comment: 

Comment Issue No. 1: Include the 

Raytheon (Military) Models A200 (C–

12A) and A200 (C–12C) Airplanes in the 

List of ‘‘Airplanes Affected’’

One commenter writes that the 

applicability of the proposed AD needs 

to be expanded. The commenter 

explains that the Raytheon military 

Models A200 (C–12A) and A200 (C–

12C) airplanes with standard landing 

gear have the same actuator assemblies 

as the airplanes listed in the NPRM, and 

could have the affected P/N nut 

installed. 

We disagree with the commenter that 

the applicability of the proposed AD 

needs to be expanded. Although a 

limited number of the affected actuator 

assemblies were installed on Models 

A200 (C–12A) and A200 (C–12C) 

airplanes, the military operates these 

airplanes and removed the affected parts 

from service before the issuance of the 

NPRM. Paragraph (e)(4) of this AD 

prohibits the subject actuator nut 

assembly from being installed on these 

airplanes in the future. The AD specifies 

that it applies to the subject actuator nut 

assembly ‘‘installed on, but not limited 

to’’ specific models listed. 

We are not changing the final rule AD 

based on this comment. 

Comment Issue No. 2: Clarify 

Applicability of AD by Identifying 

Raytheon as the Manufacturer of the 

Affected Airplane Models 

Two commenters recommend that it 

should be stated at the beginning of the 

document that these defective parts are 

installed on Raytheon airplanes. The 

commenter explains that stating this 

early in the AD action would be better 

form and result in a more easily 

comprehended document. 

The FAA agrees with the commenters. 

We will change the final rule to clearly 

identify that the affected actuator 


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