52006 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–12797 (67 FR 

44527, July 3, 2002) and by adding a 

new airworthiness directive, 

Amendment 39–14242, to read as 

follows: 

2005–18–02 Pratt & Whitney: Amendment 

39–14242. Docket No. 98–ANE–43–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 28, 2006. 

Affected ADs 

(b) This AD supersedes AD 2002–13–09. 

Applicability 

(c) This AD applies to Pratt & Whitney 

(PW) JT8D–209, –217, –217A, –217C, and 

–219 turbofan engines. These engines are 

installed on, but not limited to Boeing 727 

and McDonnell Douglas MD–80 series 

airplanes. 

Unsafe Condition 

(d) This AD results from the need to 

require enhanced inspection of selected 

critical life-limited parts of JT8D–209, –217, 

–217A, –217C, and ‘‘219 turbofan engines. 

We are issuing this AD to prevent critical 

life-limited rotating engine part failure, 

which could result in an uncontained engine 

failure and damage to 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. 

(f) Within the next 30 days after the 

effective date of this AD, (1) revise the Time 

Limits section (TLS) of the manufacturer’s 

Engine Manual, Part Number 773128, as 

appropriate for PW JT8D–209, –217, –217A, 

–217C, and –219 turbofan engines, and (2) for 

air carriers, revise the approved mandatory 

inspections section of the continuous 

airworthiness maintenance program, by 

adding the following: 

‘‘Critical Life Limited Part Inspection 

A. Inspection Requirements: 

(1) This section contains the definitions for 

individual engine piece-parts and the 

inspection procedures, which are necessary, 

when these parts are removed from the 

engine. 

(2) It is necessary to do the inspection 

procedures of the piece-parts in Paragraph B 

when: 

(a) The part is removed from the engine 

and disassembled to the level specified in 

paragraph B and 

(b) The part has accumulated more than 

100 cycles since the last piece part 

inspection, provided that the part is not 

damaged or related to the cause of its 

removal from the engine. 

(3) The inspections specified in this 

section do not replace or make unnecessary 

other recommended inspections for these 

parts or other parts. 

B. Parts Requiring Inspection. 

Note: Piece part is defined as any of the 

listed parts with all the blades removed. 

Description Section Inspection No. 

Hub (Disk), 1st Stage Compressor: 

Hub Detail—All P/Ns ........................................................................................................................................ 72–33–31 –02, –03, –04 

Hub Assembly—All P/Ns .................................................................................................................................. 72–33–31 –02, –03, –04 

Disk, 13th Stage Compressor—All P/Ns ................................................................................................................. 72–36–47 –02 

HP Turbine, First Stage: 

Rotor Assembly—All P/Ns ................................................................................................................................ 72–52–02 –04 

Disk—All P/Ns .................................................................................................................................................. 72–52–02 –03 

Disk, 2nd Stage Turbine—All P/Ns ......................................................................................................................... 72–53–16 –02 

Disk, 3rd Stage Turbine—All P/Ns .......................................................................................................................... 72–53–17 –02 

Disk, 4th Stage Turbine—All P/Ns .......................................................................................................................... 72–53–18 –02 

Alternative Methods of Compliance 

(g) You must perform these mandatory 

inspections using the TLS and the applicable 

Engine Manual unless you receive approval 

to use an alternative method of compliance 

under paragraph (h) of this AD. Section 43.16 

of the Federal Aviation Regulations (14 CFR 

43.16) may not be used to approve alternative 

methods of compliance or adjustments to the 

times in which these inspections must be 

performed. 

(h) The Manager, Engine Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Maintaining Records of the Mandatory 

Inspections 

(i) You have met the requirements of this 

AD by using a TLS of the manufacturer’s 

engine manual changed as specified in 

paragraph (f) of this AD, and, for air carriers 

operating under part 121 of the Federal 

Aviation Regulations (14 CFR part 121), by 

modifying your continuous airworthiness 

maintenance plan to reflect those changes. 

You must maintain records of the mandatory 

inspections that result from those changes to 

the TLS according to the regulations 

governing your operation. You do not need 

to record each piece-part inspection as 

compliance to this AD. For air carriers 

operating under part 121, you may use either 

the system established to comply with 

section 121.369 or use an alternative system 

that your principal maintenance inspector 

has accepted if that alternative system: 

(1) Includes a method for preserving and 

retrieving the records of the inspections 

resulting from this AD; and 

(2) Meets the requirements of section 

121.369(c); and 

(3) Maintains the records either 

indefinitely or until the work is repeated. 

(j) These record keeping requirements 

apply only to the records used to document 

the mandatory inspections required as a 

result of revising the TLS as specified in 

paragraph (f) of this AD, and do not alter or 

amend the record keeping requirements for 

any other AD or regulatory requirement. 

Related Information 

(k) None. 

Issued in Burlington, Massachusetts, on 

August 24, 2005. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17319 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21599; Directorate 

Identifier 2005–NM–036–AD; Amendment 

39–14246; AD–2005–18–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–2B19 (Regional Jet 

Series 100 & 440) 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 

CL–600–2B19 series airplanes. That AD 

currently requires revising the airplane 

flight manual (AFM) to provide the 

flightcrew with operating limitations 

and procedures to enable them to 

maintain controllability of the airplane 

in the event that aileron control stiffness 

is encountered during flight. This new 

AD requires revising the Airworthiness 

Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 52007 

Limitations section of the Instructions of 

Continued Airworthiness to incorporate 

certain repetitive tasks for the aileron 

control system and requires a briefing to 

advise flightcrews that certain aileron 

control checks are no longer required. 

After accomplishing the applicable 

initial tasks, the existing AFM revisions 

for the aileron control check may be 

removed from the AFM. This AD results 

from the development of terminating 

actions for the AFM revisions. We are 

issuing this AD to prevent aileron 

control stiffness during flight, which 

could result in reduced or possible loss 

of controllability of the airplane. 

DATES: This AD becomes effective 

October 6, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of Canadair Regional Jet Temporary 

Revision 2B–2068, dated December 13, 

2004, listed in the AD as of October 6, 

2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of Canadair Regional Jet TR RJ/109–2, 

dated August 9, 2002, as of October 10, 

2002 (67 FR 60117, September 25, 

2002). 

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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, 

Station Centre-ville, Montreal, Quebec 

H3C 3G9, Canada, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: Dan 

Parillo, Aerospace Engineer, Systems 

and Flight Test Branch, ANE–172, FAA, 

New York Aircraft Certification Office, 

1600 Stewart Avenue, Westbury, suite 

410, New York 11590; telephone (516) 

228–7305; fax (516) 794–5531. 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2002–19–07, amendment 

39–12887 (67 FR 60117, September 25, 

2002). The existing AD applies to all 

Bombardier Model CL–600–2B19 series 

airplanes. That NPRM was published in 

the Federal Register on June 22, 2005 

(70 FR 36067). That NPRM proposed to 

retain the requirements of the existing 

AD (i.e., airplane flight manual (AFM) 

revisions). That NPRM also proposed to 

require revising the Airworthiness 

Limitations section of the Instructions of 

Continued Airworthiness to incorporate 

certain repetitive tasks for the aileron 

control system and briefing flightcrews 

that certain aileron control checks are 

no longer required. After accomplishing 

the applicable initial tasks, the existing 

AFM revisions for the aileron control 

check may be removed from the AFM. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Conclusion 

We have carefully reviewed the 

available data and determined that air 

safety and the public interest require 

adopting the AD as proposed. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered airplanes 

Fleet cost 

AFM revisions (required by AD 2002–19–07) ................... 1 $65 None ........ $65 727 $47,255 

Airworthiness Limitation revision (new action) .................. 1 $65 None ........ $65 727 $47,255 

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: 

52008 Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 

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 removing amendment 39–12887 (67 

FR 60117, September 25, 2002) and by 

adding the following new airworthiness 

directive (AD): 

2005–18–06 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–14246. 

Docket No. FAA–2005–21599; 

Directorate Identifier 2005–NM–036–AD. 

Effective Date 

(a) This AD becomes effective October 6, 

2005. 

Affected ADs 

(b) This AD supersedes AD 2002–19–07. 

Applicability 

(c) This AD applies to all Bombardier 

Model CL–600–2B19 (Regional Jet series 100 

& 440) 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 (m) 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 the 

development of terminating actions for the 

airplane flight manual (AFM) revisions. We 

are issuing this AD to prevent aileron control 

stiffness during flight, which could result in 

the reduction or possible loss of 

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 2002–19–07 

AFM Revisions 

(f) Within 14 days after October 10, 2002 

(the effective date of AD 2002–19–07), insert 

the procedures for aileron system jams 

specified in Canadair Regional Jet Temporary 

Revision (TR) RJ/109–2, dated August 9, 

2002, into the Emergency Procedures and 

Abnormal Procedures Sections, as applicable, 

of the FAA-approved Canadair Regional Jet 

AFM. 

(g) Upon the accumulation of 5,000 total 

flight hours, or within 14 days after October 

10, 2002, whichever occurs later, insert the 

procedures for the aileron control check 

specified in Canadair Regional Jet TR RJ/109–

2, dated August 9, 2002, into the Limitations 

and Normal Procedures Sections, as 

applicable, of the Canadair Regional Jet AFM. 

Note 2: The Limitations and Normal 

Procedures specified by paragraph (g) of this 

AD are required to be implemented only 

when an airplane has accumulated 5,000 

total flight hours. However, individual pilots 

may operate other airplanes that have not yet 

accumulated 5,000 total flight hours, and that 

are not subject to those limitations and 

procedures. Therefore, to avoid any 

confusion or misunderstanding, it is 

important that airlines have communication 

mechanisms in place to ensure that pilots are 

aware, for each flight, whether the 

Limitations and Normal Procedures apply. 

(h) When the information in Canadair 

Regional Jet TR RJ/109–2, dated August 9, 

2002, of the Canadair Regional Jet AFM, has 

been incorporated into the FAA-approved 

general revisions of the AFM, the TR may be 

removed from the AFM. 

New Actions Required by This AD 

Revision of Airworthiness Limitations (AWL) 

Section 

(i) Within 60 days after the effective date 

of this AD, revise the AWL section of the 

Instructions of Continued Airworthiness by 

incorporating the tasks specified in Table 1 

of this AD and the corresponding ‘‘Task 

Threshold/Interval’’ of Canadair Regional Jet 

TR 2B–2068, dated December 13, 2004, into 

Appendix B—Airworthiness Limitations of 

Part 2 of Canadair Regional Jet Model CL–

600–2B19 Maintenance Requirements 

Manual. Thereafter, except as provided in 

paragraph (m) of this AD, no alternative 

lubrication/replacement intervals may be 

approved for the aileron control system. After 

accomplishing the applicable initial tasks, 

the AFM revisions for the aileron control 

check required by paragraph (g) of this AD 

and allowed by paragraph (h) of this AD may 

be removed from the AFM. 

TABLE 1.—AFFECTED TASK NUMBERS

Task No. Description 

(1) R22–11–A083–01 .................. Lubrication of aileron autopilot servo and servo mount engage clutch faces. 

(2) R27–00–A053–01 .................. Replacement of aileron control pulleys with new or serviceable parts. 

(3) R27–11–A082–01 .................. Lubrication of the aileron control cables at the wing pulley interfaces. 

(4) R27–11–A082–02 .................. Lubrication of the aileron rear quadrant and trim lever bearings. 

(j) For airplanes that have exceeded the 

task threshold for the new tasks specified in 

paragraph (i) of this AD as of the effective 

date of this AD: Do the initial tasks at the 

applicable ‘‘Phase-In’’ time specified in 

Canadiar Regional Jet TR 2B–2068, dated 

December 13, 2004; except where the TR 

specifies accomplishing the task no later than 

the applicable compliance time ‘‘from 

November 5, 2004,’’ this AD requires 

accomplishing the task within the applicable 

compliance time ‘‘after the effective date of 

this AD.’’

(k) When the information in Canadair 

Regional Jet TR 2B–2068, dated December 13, 

2004, is included in the general revisions of 

the maintenance requirements manual, this 

TR may be removed. 

Flightcrew Briefing 

(l) After accomplishing the applicable 

initial tasks required by paragraph (i) of this 

AD, brief flightcrews that there is no longer 

a requirement to perform aileron control 

checks following takeoff from a wet or 

contaminated runway. 

Alternative Methods of Compliance (AMOCs) 

(m) 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 

(n) Canadian airworthiness directive CF–

2002–35R2, issued January 6, 2005, also 

addresses the subject of this AD. 

Material Incorporated by Reference 

(o) You must use Canadair Regional Jet TR 

RJ/109–2, dated August 9, 2002; and 

Canadair Regional Jet Temporary Revision 

2B–2068, dated December 13, 2004, to the 

Canadair Regional Jet Model CL–600–2B19 

Maintenance Requirements Manual; as 

applicable; to perform the actions that are 

required by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Canadair Regional Jet Temporary Revision 

2B–2068, dated December 13, 2004, in 

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

part 51. 

(2) The Director of the Federal Register 

approved the incorporation by reference of 

Canadair Regional Jet TR RJ/109–2, dated 

Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Rules and Regulations 52009 

August 9, 2002, as of October 10, 2002 (67 

FR 60117, September 25, 2002). 

(3) 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 

24, 2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–17333 Filed 8–31–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21595; Directorate 

Identifier 2002–NM–321–AD; Amendment 

39–14245; AD 2005–18–05] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–215–1A10 (Water Bomber), 

CL–215–6B11 (CL215T Variant), and 

CL–215–6B11 (CL415 Variant) 

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 certain Bombardier 

Model CL–215–1A10 and CL–215–6B11 

series airplanes. That AD currently 

requires repetitive ultrasonic 

inspections to detect cracking of the 

lower caps of the wing front spar and 

rear spar, and corrective action if 

necessary. This new AD reduces the 

threshold to do the initial inspections 

and revises the repetitive inspection 

interval. This new AD also adds a 

repetitive ultrasonic inspection of the 

wing lower skin. This AD results from 

reports of cracks in the front and rear 

spar lower caps. We are issuing this AD 

to detect and correct cracking of the 

lower caps of the wing front spar and 

rear spar, which could result in reduced 

structural integrity of the airplane. 

DATES: This AD becomes effective 

October 6, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 6, 2005. 

On March 4, 1998 (63 FR 7640, 

February 17, 1998), the Director of the 

Federal Register approved the 

incorporation by reference of Canadair 

Alert Service Bulletin 215–A454, 

Revision 1, dated May 25, 1995; and 

Canadair Alert Service Bulletin 215–

A463, Revision 1, dated May 25, 1995. 

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 Bombardier, Inc., Canadair, 

Aerospace Group, P.O. Box 6087, 

Station Centreville, Montreal, Quebec 

H3C 3G9, Canada, for service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

David Lawson, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, suite 410, Westbury, New York 

11590; telephone (516) 228–7327; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Examining the Docket 

You may 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 street 

address stated in the ADDRESSES section. 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 98–04–08, amendment 

39–10321 (63 FR 7640, February 17, 

1998). The existing AD applies to 

certain Bombardier Model CL–215–

1A10 and CL–215–6B11 series 

airplanes. That NPRM was published in 

the Federal Register on June 22, 2005 

(70 FR 36075). That NPRM proposed to 

continue to require repetitive ultrasonic 

inspections to detect cracking of the 

lower caps of the wing front spar and 

rear spar, and corrective action if 

necessary. That NPRM also proposed to 

require reducing the threshold in the 

existing AD for doing the initial 

inspections and revising the repetitive 

inspection interval, and to add a 

repetitive ultrasonic inspection of the 

wing lower skin. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. No comments 

have been received on the NPRM or on 

the determination of the cost to the 

public. 

Explanation of Change in Applicability 

We have revised the applicability of 

the final rule 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, 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 burden on any 

operator nor increase the scope of the 

AD. 

Costs of Compliance 

This AD affects about 3 airplanes of 

U.S. registry. 

The actions that are required by AD 

98–04–08 and retained in this AD take 

about 16 work hours per airplane, at an 

average labor rate of $65 per work hour. 

Based on these figures, the estimated 

cost of the currently required actions is 

$1,040 per airplane, per inspection 

cycle. 

The new inspections required by this 

AD will 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 new 

inspections specified in this AD for U.S. 

operators is $195 per inspection cycle, 

or $65 per airplane, per inspection 

cycle. 

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