48854 Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations 

reduced directional control—particularly 

during a rejected takeoff. 

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. 

Installation of Hydraulic Line Shields 

(f) Within 24 months after the effective 

date of this AD, install additional shielding 

of the hydraulic lines in the wing box area, 

by doing all the actions specified in the 

Accomplishment Instructions of Bombardier 

Service Bulletin 601R–57–021, Revision D, 

dated July 11, 2005. 

(g) Installations accomplished before the 

effective date of this AD according to 

Bombardier Service Bulletin 601R–57–021, 

Revision ‘‘B,’’ dated July 18, 2001; or 

Revision ‘‘C,’’ dated February 23, 2004; are 

considered acceptable for compliance with 

the corresponding action specified in this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Related Information 

(i) Canadian airworthiness directive CF–

2004–20, dated October 5, 2004, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(j) You must use Bombardier Service 

Bulletin 601R–57–021, Revision D, dated July 

11, 2005, 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 this document 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 

Centreville, 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.

Issued in Renton, Washington, on August 

10, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 05–16264 Filed 8–19–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2005–20730; Directorate 

Identifier 2004–NM–68–AD; Amendment 39–

14172; AD 2005–13–35] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model DHC–8–100, DHC–8–200, and 

DHC–8–300 Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to all Bombardier Model 

DHC–8–100, DHC–8–200, and DHC–8–

300 series airplanes. That AD currently 

requires installation of a placard on the 

instrument panel of the cockpit to 

advise the flightcrew that positioning of 

the power levers below the flight idle 

stop during flight is prohibited. 

Additionally, the existing AD requires 

eventual installation of an FAAapproved system that would prevent 

such positioning of the power levers 

during flight. Installation of that system 

terminates the requirement for 

installation of a placard. This new AD 

requires operators who have 

incorporated a certain Bombardier 

service bulletin to perform repetitive 

operational checks of the beta lockout 

system and to revise the Airworthiness 

Limitations document. This AD is 

prompted by in-service issues reported 

by operators who incorporated 

Bombardier Service Bulletin 8–76–24 as 

an alternative method of compliance to 

the existing AD. We are issuing this AD 

to prevent the inadvertent activation of 

ground beta mode during flight, which 

could lead to engine overspeed, engine 

damage or failure, and consequent 

reduced controllability of the airplane.

DATES: This AD becomes effective 

September 26, 2005. 

The incorporation by reference of 

certain publications listed in the AD is 

approved by the Director of the Federal 

Register as of September 26, 2005.

ADDRESSES: For service information 

identified in this AD, contact 

Bombardier, Inc., Bombardier Regional 

Aircraft Division, 123 Garratt Boulevard, 

Downsview, Ontario M3K 1Y5, Canada. 

Docket: The AD docket contains the 

proposed AD, comments, and any final 

disposition. You can examine the 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 U.S. Department of Transportation, 

400 Seventh Street SW., room PL–401, 

Washington, DC. This docket number is 

FAA–2005–20730; the directorate 

identifier for this docket is 2004–NM–

68–AD.

FOR FURTHER INFORMATION CONTACT:

Richard Fiesel, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, Federal Aviation Administration, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, Suite 410, 

Westbury, New York 11590; telephone 

(516) 228–7304; fax (516) 794–5531.

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend part 39 of the 

Federal Aviation Regulations (14 CFR 

part 39) with an AD to supersede AD 

2000–02–13, amendment 39–11531 (65 

FR 4095, January 26, 2000). The existing 

AD applies to all Bombardier Model 

DHC–8–101, –102, –103, –106, –201, 

–202, –301, –311, and –315 airplanes. 

The proposed AD was published in the 

Federal Register on March 30, 2005 (70 

FR 16164), to continue to require 

installation of a placard on the 

instrument panel of the cockpit and 

eventual installation of an FAAapproved system to prevent positioning 

of the power levers below the flight idle 

stop. The proposed AD would also 

require operators who have 

incorporated a certain Bombardier 

service bulletin to perform repetitive 

operational checks of the beta lockout 

system and to revise the Airworthiness 

Limitations document. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comment that has been 

submitted on the proposed AD. The 

commenter supports the proposed AD. 

Explanation of Change to Applicability 

We have revised the applicability of 

the proposed AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has been submitted, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously. 

We have determined that this change 

will neither increase the economic 

Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations 48855

burden on any operator nor increase the 

scope of the AD. 

Costs of Compliance 

This AD affects about 185 Bombardier 

Model DHC–8–101, –102, –103, –106, 

–201, –202, –301, –311, and –315 

airplanes of U.S. registry. 

The installation of a placard that is 

required by AD 2000–02–13, and 

retained in this AD, requires about 1 

work hour per airplane, at an average 

labor rate of $65 per work hour. No 

parts are required. Based on these 

figures, the cost impact of the placard 

installation on U.S. operators is 

estimated to be $12,025, or $65 per 

airplane. 

The installation of the preventative 

system that is required by AD 2000–02–

13, and retained in this AD, requires 

about 123 work hours per airplane, at an 

average labor rate of $65 per work hour. 

We estimate that required parts will cost 

approximately $12,000 per airplane. 

Based on these figures, the cost impact 

of the installation of the preventative 

system on U.S. operators is estimated to 

be $3,699,075, or $19,995 per airplane. 

The operational check of the beta 

lockout system will take about 1 work 

hour per airplane, per check cycle, at an 

average labor rate of $65 per work hour. 

No parts are required. Based on these 

figures, the estimated cost of the new 

operational check specified in this AD 

for U.S. operators is $12,025, or $65 per 

airplane, per check cycle. 

The revision of the Airworthiness 

Limitations document would take about 

1 work hour per airplane, at an average 

labor rate of $65 per work hour. Based 

on these figures, the estimated cost of 

the revision specified in the AD for U.S. 

operators is $12,025, or $65 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. 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 FAA amends § 39.13 by 

removing amendment 39–11531 (65 FR 

4095, January 26, 2000) and by adding 

the following new airworthiness 

directive (AD):

2005–13–35 Bombardier, Inc. (Formerly de 

Havilland, Inc.): Amendment 39–14172. 

Docket No. FAA–2005–20730; 

Directorate Identifier 2004–NM–68–AD. 

Effective Date 

(a) This AD becomes effective September 

26, 2005. 

Affected ADs 

(b) This AD supersedes AD 2000–02–13, 

amendment 39–11531. 

Applicability 

(c) This AD applies to all Bombardier 

Model DHC–8–100, DHC–8–200, and DHC–

8–300 series 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 revision. In this 

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

the operator must request approval for an 

alternative method of compliance in 

accordance with paragraph (l)(1) 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 was prompted by in-service 

issues reported by operators who 

incorporated a certain Bombardier service 

bulletin as an alternative method of 

compliance to AD 2000–02–13. We are 

issuing this AD to prevent the inadvertent 

activation of ground beta mode during flight, 

which could lead to engine overspeed, 

engine damage or failure, and consequent 

reduced controllability of the airplane. 

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. 

Requirements of AD 2000–02–13

Installation of Placard 

(f) Within 30 days after March 1, 2000 (the 

effective date of AD 2000–02–13), install a 

placard in a prominent location on the 

instrument panel of the cockpit that states:

‘‘Positioning of the power levers below the 

flight idle stop during flight is prohibited. 

Such positioning may lead to loss of airplane 

control, or may result in an engine overspeed 

condition and consequent loss of engine 

power.’’

Installation of System Preventing Excessive 

Lowering of Power Levers in Flight 

(g) Within 2 years after March 1, 2000, 

install a system that would prevent 

positioning the power levers below the flight 

idle stop during flight, in accordance with a 

method approved by the Manager, New York 

Aircraft Certification Office (ACO), FAA. 

Following accomplishment of that 

installation, the placard required by 

paragraph (f) of this AD may be removed. 

(h) In the event that the system required by 

paragraph (g) of this AD malfunctions, or if 

the use of an override (if installed) is 

necessary, the airplane may be operated for 

three days to a location where required 

maintenance/repair can be performed, 

provided the system required by paragraph 

(g) of this AD has been properly deactivated 

and placarded for flightcrew awareness, in 

accordance with the FAA-approved Master 

Minimum Equipment List (MMEL).

48856 Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations 

New Requirements of This AD 

Operational Checks of the Beta Lockout 

System 

(i) For airplanes that have been modified 

in accordance with Bombardier Service 

Bulletin 8–76–24: Within 50 flight hours after 

the effective date of this AD, perform an 

operational check of the beta lockout system 

in accordance with the applicable de 

Havilland Dash 8 task card listed in Table 1 

of this AD. Thereafter repeat the operational 

check at intervals specified in the applicable 

de Havilland temporary revision (TR) listed 

in Table 2 of this AD.

TABLE 1.—TASK CARDS

DHC–8 model de Havilland task card Date 

–101, –102, –103, and –106 airplanes ................................. Dash 8 Series 100 Maintenance Task Card 6120/10 ........... November 21, 2003. 

–201 and –202 airplanes ....................................................... Dash 8 Series 200 Maintenance Task Card 6120/10 ........... November 21, 2003. 

–301, –311, and –315 airplanes ............................................ Dash 8 Series 300 Maintenance Task Card 6120/10 ........... November 21, 2003. 

Revision of Airworthiness Limitations (AWL) 

Section 

(j) Within 30 days after the effective date 

of this AD, revise the AWL section of the 

applicable Instructions for Continued 

Airworthiness by incorporating the contents 

of the applicable de Havilland TR listed in 

Table 2 of this AD into the AWL section of 

the applicable Bombardier DHC–8 

Maintenance Program Support Manual 

(PSM).

TABLE 2.—TRS

DHC–8 model de Havilland 

TR Dated For PSM 

–101, –102, –103, and –106 airplanes ........................................................................................... AWL–86 ...... March 17, 2003 1–8–7 

–201 and –202 airplanes ................................................................................................................ AWL 2–26 ... March 17, 2003 1–82–7 

–301, –311, and –315 airplanes ..................................................................................................... AWL 3–93 ... March 17, 2003 1–83–7 

(k) When the information in the applicable 

de Havilland TR identified in Table 2 of this 

AD has been included in the general 

revisions of the applicable PSM identified in 

Table 2 of this AD, the general revisions may 

be inserted in the PSM, and the applicable 

TR may be removed from the AWL section 

of the Instruction for Continued 

Airworthiness. 

Alternative Methods of Compliance (AMOCs) 

(l)(1) The Manager, New York ACO has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(2) AMOCS approved previously in 

accordance with AD 2000–02–13 are 

acceptable for the corresponding 

requirements of this AD. 

Materials Incorporated by Reference 

(m) You must use the documents listed in 

Table 3 of this AD to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approves the incorporation 

by reference of these documents in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. To get copies of the service 

information, contact Bombardier, Inc., 

Bombardier Regional Aircraft Division, 123 

Garratt Boulevard, Downsview, Ontario M3K 

1Y5, Canada. To view the AD docket, go to 

the Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

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

Washington, DC. To review copies of the 

service information, go to 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.—MATERIAL INCORPORATED BY REFERENCE

de Havilland service information Dated 

To de Havilland 

program support 

manual 

Dash 8 Series 100 Maintenance Task Card 6120/10 ................................................................................ November 21, 2003 1–8–7TC. 

Dash 8 Series 200 Maintenance Task Card 6120/10 ................................................................................ November 21, 2003 1–82–7TC. 

Dash 8 Series 300 Maintenance Task Card 6120/10 ................................................................................ November 21, 2003 1–83–7TC. 

Temporary Revision AWL–86 .................................................................................................................... March 17, 2003 ...... 1–8–7. 

Temporary Revision AWL 2–26 ................................................................................................................. March 17, 2003 ...... 1–82–7. 

Temporary Revision AWL 3–93 ................................................................................................................. March 17, 2003 ...... 1–83–7. 

Federal Register / Vol. 70, No. 161 / Monday, August 22, 2005 / Rules and Regulations 48857

Issued in Renton, Washington, on June 21, 

2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–12841 Filed 8–19–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2005–20968; Directorate 

Identifier 94–CE–15–AD; Amendment 39–

14222; AD 95–19–15 R1] 

RIN 2120–AA64

Airworthiness Directives; Tiger Aircraft 

LLC Models AA–5, AA–5A, AA–5B, and 

AG–5B Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: The FAA is revising 

Airworthiness Directive (AD) 95–19–15 

for all Tiger Aircraft LLC (Type 

Certificate A16EA formerly held by 

American General Aircraft Corporation 

and Grumman American Aviation 

Corporation) Models AA–5, AA–5A, 

AA–5B, and AG–5B airplanes. AD 95–

19–15 currently requires you to inspect 

the wing attach shoulder bolts for 

fretting, scoring, wear, or enlarged or 

elongated mounting holes (known as 

damage from hereon); replace any 

damaged parts; repair any damaged 

areas; inspect the wing spar at the center 

spar clearance gap for excessive 

clearance; and shim the spar if excessive 

clearance is found. That AD was written 

to apply to all serial numbers of all 

models. A design change was made in 

this area beginning with serial number 

10175 of the Model AG–5B airplanes. 

Therefore, the action should not apply 

to Model AG–5B airplanes with a serial 

number of 10175 or higher. This AD 

retains all the actions of AD 95–19–15 

for all airplanes originally affected, but 

cuts off the applicability for the Model 

AG–5B airplanes at serial number 

10174. We are issuing this AD to 

continue to prevent wing attach 

shoulder bolt failure, which, if not 

detected and corrected, could lead to 

structural damage of the wing/fuselage 

to the point of failure.

DATES: This AD becomes effective on 

October 3, 2005. 

As of October 3, 2005, 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 Tiger Aircraft LLC, 226 Pilot 

Way, Martinsburg, WV 25401. 

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–2005–20968; Directorate Identifier 

94–CE–15–AD.

FOR FURTHER INFORMATION CONTACT:

Richard Beckwith, Aerospace Engineer, 

New York Aircraft Certification Office 

(ACO), 1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone: 516–

794–5531; facsimile: 516–794–5531.

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD?

The FAA has received four reports 

(three in England and one in the United 

States) of wing attach shoulder bolt 

failure on Tiger Aircraft LLC (Type 

Certificate A16EA formerly held by 

American General Aircraft Corporation 

(AGAC) and Grumman American 

Aviation Corporation (GAAC)) Models 

AA–5, AA–5A, AA–5B, and AG–5B 

airplanes. Investigation reveals that 

excessive wing to center spar clearance 

could have contributed to the bolt 

failures; however, in each of the four 

instances, the bolts failed before 

reaching the service life of 7,250 hours 

time-in-service (TIS). The FAA has 

determined that, to assure the safety of 

these airplanes, the established service 

life of these bolts needed review. Our 

review of service life on Tiger Aircraft 

LLC (Type Certificate A16EA formerly 

held by AGAC and GAAC) Models AA–

5, AA–5A, AA–5B, and AG–5B 

airplanes caused us to issue AD 95–19–

15, Amendment 39–9377 (60 FR 48628, 

September 20, 1995). AD 95–19–15 

currently requires the following on 

Tiger Aircraft LLC (Type Certificate 

A16EA formerly held by AGAC and 

GAAC) Models AA–5, AA–5A, AA–5B, 

and AG–5B airplanes, all serial 

numbers:

—Inspect the wing attach shoulder bolts 

for fretting, scoring, wear, or enlarged 

or elongated mounting holes (known 

as damage from hereon), and replace 

any damaged parts and repairing any 

damaged areas; 

—Inspect the wing spar at the center 

spar clearance gap for excessive 

clearance; and 

—Shim the spar if excessive clearance is 

found.

AD 95–19–15 was written to apply to 

all serial numbers of all models. A 

design change was made in this area 

beginning with serial number 10175 of 

the Model AG–5B airplanes. Therefore, 

FAA determined that the action should 

not apply to Model AG–5B airplanes 

with a serial number of 10175 or higher. 

Has FAA taken any action to this 

point? 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 all Tiger 

Aircraft LLC (Type Certificate A16EA 

formerly held by American General 

Aircraft Corporation and Grumman 

American Aviation Corporation) Models 

AA–5, AA–5A, AA–5B, and AG–5B 

airplanes. This proposal was published 

in the Federal Register as a notice of 

proposed rulemaking (NPRM) on May 

19, 2005 (70 FR 28854). The NPRM 

proposed to retain all the actions of AD 

95–19–15 for all airplanes originally 

affected, but proposed to cut off the 

applicability for the Model AG–5B 

airplanes at serial number 10174. 

Comments 

Was the public invited to comment?

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: Type Certificate 

Data Sheet (TCDS) Number (No.) Is 

Referenced Incorrectly in the NPRM 

What is the commenter’s concern? A 

letter from Tiger Aircraft LLC notes that 

the TCDS No. A16EH in the NPRM is 

referenced incorrectly. The TCDS 

should be No. A16EA. 

What is FAA’s response to the 

concern? We concur. We will correct all 

reference in the final rule of the TCDS 

to No. A16EA. 

Comment Issue No. 2: Manufacturer’s 

Contact Information Is Incorrect in the 

NPRM 

What is the commenter’s concern?

The commenter from Tiger Aircraft LLC 

requests that FAA change the contact 

information to that for Tiger Aircraft 

LLC. American General Aircraft 

Corporation is out of business. 

What is FAA’s response to the 

concern? The FAA concurs. We will 

change the contact information in the 

final rule to show Tiger Aircraft LLC. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

the changes discussed above and minor 

editorial corrections. We have