43032 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations 

Actions Compliance Procedures 

(3) Do not install any heater fuel pump (model 

91E92–1 or model 91E93–1) unless you 

have visually inspected the pump for leakage 

and corrected any abnormalities specified in 

paragraph (e)(2) of the AD.

As of June 20, 2003 (the effective date of AD 

2003–11–14).

Follow The New Piper Aircraft, Inc. Service 

Bulletin No. 1127, dated February 26, 2003, 

and Kelly Aerospace Power Systems Service Information Letter Bulletin No. A–110A, 

dated March 6, 2003. 

(f) What actions must I do to address this 

problem for Group 2 airplanes? To address 

this problem for Group 2 airplanes, you must 

do the following:

Actions Compliance Procedures 

(1) Visually inspect any installed aircraft heater 

fuel pump (model 91E92–1 or model 91E93–

1) for leakage.

Within the next 10 hours time-in-service (TIS), 

after August 26, 2005 (the effective date of 

this AD), unless already done.

Follow The New Piper Aircraft, Inc. Service 

Bulletin No. 1127B, dated April 18, 2005, 

and Kelly Aerospace Power Systems Service Information Letter Bulletin No. A–110B, 

dated December 20, 2004. 

(2) If any leak is found, inspect the pump sealing surface for abnormalities (for example, 

nicks, gouges, or warping). Correct any abnormality found. If any abnormality cannot be 

corrected, replace the heater fuel pump.

Before further flight after the inspection required in paragraph (f)(1) of this AD.Follow The New Piper Aircraft, Inc. Service 

Bulletin No. 1127B, dated April 18, 2005, 

and Kelly Aerospace Power Systems Service Information Letter Bulletin No. A–110B, 

dated December 20, 2004. 

(3) Do not install any heater fuel pump (model 

91E92–1 or model 91E93–1) unless you 

have visually inspected the pump for leakage 

and corrected any abnormalities specified in 

paragraph (f)(2) of this AD.

As of August 26, 2005 (the effective date of 

this AD).

Follow The New Piper Aircraft, Inc. Service 

Bulletin No. 1127B, dated April 18, 2005, 

and Kelly Aerospace Power Systems Service Information Letter Bulletin No. A–110B, 

dated December 20, 2004. 

May I Request an Alternative Method of 

Compliance? 

(g) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Atlanta Aircraft Certification Office 

(ACO). For information on any already 

approved alternative methods of compliance, 

contact Hector Hernandez, Aerospace 

Engineer, FAA, Atlanta Aircraft Certification 

Office, One Crown Center, 1895 Phoenix 

Boulevard, Suite 450, Atlanta, Georgia 30349; 

telephone: (770) 703–6069; facsimile: (770) 

703–6097. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in The 

New Piper Aircraft, Inc. Service Bulletin No. 

1127, dated February 26, 2003; The New 

Piper Aircraft, Inc. Service Bulletin No. 

1127B, dated April 18, 2005; Kelly Aerospace 

Power Systems Service Information Letter 

Bulletin No. A–110A, dated March 6, 2003; 

and Kelly Aerospace Power Systems Service 

Information Letter Bulletin No. A–110B, 

dated December 20, 2004. 

(1) On June 20, 2003 (68 FR 33356, June 

4, 2003), and in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51, the Director of the 

Federal Register approved the incorporation 

by reference of The New Piper Aircraft, Inc. 

Service Bulletin No. 1127, dated February 26, 

2003, and Kelly Aerospace Power Systems 

Service Information Letter Bulletin No. A–

110A, dated March 6, 2003. 

(2) As of August 26, 2005, and in 

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

part 51, the Director of the Federal Register 

approved the incorporation by reference of 

The New Piper Aircraft, Inc. Service Bulletin 

No. 1127B, dated April 18, 2005, and Kelly 

Aerospace Power Systems Service 

Information Letter Bulletin No. A–110B, 

dated December 20, 2004. 

(3) To get a copy of this service 

information, contact The New Piper Aircraft, 

Inc., Customer Services, 2926 Piper Drive, 

Vero Beach, Florida 32960; telephone: (772) 

567–4361; facsimile: (772) 978–6584. To 

review copies of this service information, go 

to the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html or call (202) 741–6030. 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–

2005–21590; Directorate Identifier 2005–CE–

33–AD.

Issued in Kansas City, Missouri, on July 14, 

2005. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–14389 Filed 7–25–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21139; Directorate 

Identifier 2003–NM–196–AD; Amendment 

39–14193; AD 2005–15–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Model CL–600–1A11 (CL–600), Model 

CL–600–2A12 (CL–601), and Model CL–

600–2B16 (CL–601–3A, CL–601–3R, 

and CL–604) Airplanes

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Bombardier Model CL–600–1A11 (CL–

600), Model CL–600–2A12 (CL–601), 

and Model CL–600–2B16 (CL–601–3A, 

CL–601–3R, and CL–604) airplanes. 

This AD requires operators to assign 

serial numbers or part numbers to 

certain landing gear parts and to 

establish the number of landings on the 

parts, if necessary. This AD also 

requires operators to revise the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness to reflect the new life 

limits of the landing gear parts. This AD 

is prompted by reports that landing gear 

parts that have safe-life limits but do not 

Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations 43033

have serial numbers or part numbers 

can be removed from one landing gear 

and re-installed on another, making 

tracking difficult. We are issuing this 

AD to prevent life-limited landing gear 

parts from being used beyond their safelife limits, which could lead to collapse 

of the landing gear.

DATES: Effective August 30, 2005. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of August 30, 2005.

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:

Serge Napoleon, 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) 228–7312; 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 would 

apply to certain Bombardier Model CL–

600–1A11 (CL–600), Model CL–600–

2A12 (CL–601), and Model CL–600–

2B16 (CL–601–3A, CL–601–3R, and CL–

604) airplanes. That NPRM was 

published in the Federal Register on 

May 9, 2005 (70 FR 24331). (A 

correction of the rule was published in 

the Federal Register on May 19, 2005 

(70 FR 28988)). That NPRM proposed to 

require operators to assign serial 

numbers or part numbers to certain 

landing gear parts and to establish the 

number of landings on the parts, if 

necessary. That NPRM also proposed to 

require operators to revise the 

Airworthiness Limitations section of the 

Instructions for Continued 

Airworthiness to reflect the new life 

limits of the landing gear parts. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We received no 

comments on the NPRM or on the 

determination of the cost to the public. 

Explanation of Change to Applicability 

We have revised the applicability to 

reflect the model designations as 

published in the most recent type 

certificate data sheet. 

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 

The following table provides the 

estimated costs for U.S. operators to 

assign serial numbers or part numbers to 

certain landing gear parts to comply 

with this AD.

ESTIMATED COSTS

Model Work 

hours 

Average 

labor rate 

per hour 

Parts Cost per 

airplane 

Number of 

U.S.-registered

airplanes 

Fleet cost 

CL–600–1A11 (CL–600) .................................................................... 13 $65 None .... $845 54 $45,630 

CL–600–2A12 (CL–601), CL–600–2B16 (CL–601–3A and CL–

601–3R).

9 65 None .... 585 128 74,880 

CL–600–2B16 (CL604) ...................................................................... 5 65 None .... 325 119 38,675 

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:

43034 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 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 

adding the following new airworthiness 

directive (AD):

2005–15–04 Bombardier, Inc. (Formerly 

Canadair): Amendment 39–14193. 

Docket No. FAA–2005–21139; 

Directorate Identifier 2003-NM–196-AD. 

Effective Date 

(a) This AD becomes effective August 30, 

2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the Bombardier 

airplane models, certificated in any category, 

listed in Table 1 of this AD.

TABLE 1.—APPLICABILITY

Bombardier model— As identified in Bombardier service bulletin—

CL–600–1A11 (CL–600) airplanes ........................................................... 600–0710, Revision 01, dated December 15, 2003. 

CL–600–2A12 (CL–601) and CL–600–2B16 (CL–601–3A, and CL–

601–3R) airplanes.

601–0546, Revision 01, dated December 15, 2003. 

CL–600–2B16 (CL–604) airplanes ........................................................... 604–32–014, dated May 31, 2002. 

Unsafe Condition 

(d) This AD was prompted by reports that 

landing gear parts that have safe-life limits 

but do not have serial numbers or part 

numbers can be removed from one landing 

gear and re-installed on another, making 

tracking difficult. We are issuing this AD to 

prevent life-limited landing gear parts from 

being used beyond their safe-life limits, 

which could lead to collapse of the landing 

gear. 

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. 

Add Serial Numbers or Part Numbers 

(f) At the applicable compliance time 

specified in paragraph (f)(1), (f)(2), or (f)(3) of 

this AD: Add serial numbers and part 

numbers, as applicable, to the parts 

identified in the service bulletins. Do all 

actions in accordance with the applicable 

service bulletin.

(1) For parts identified in the Bombardier 

Service Bulletin 600–0710, Revision 01, 

dated December 15, 2003; and Bombardier 

Service Bulletin 601–0546, Revision 01, 

dated December 15, 2003; as having a 

compliance time of ‘‘five years for the parts 

listed in Part A’: Within 60 months after the 

effective date of this AD. 

(2) For parts identified in Bombardier 

Service Bulletin 600–0710, Revision 01, 

dated December 15, 2003; and Bombardier 

Service Bulletin 601–0546, Revision 01, 

dated December 15, 2003; as having a 

compliance time of ‘‘ten years for the parts 

listed in Part B’: Within 120 months after the 

effective date of this AD. 

(3) For parts identified in the Bombardier 

Service Bulletin 604–32–014, dated May 31, 

2002, as having a compliance time of ‘‘no 

later than a calendar time of 8 years’: Within 

96 months after the effective date of this AD.

Note 1: The Bombardier service bulletins 

refer to the Messier-Dowty service bulletins 

in Table 2 of this AD as additional sources 

of service information for adding part 

numbers or serial numbers by vibro-peening 

the numbers on main landing gear (MLG) and 

nose landing gear (NLG) components that do 

not have them; and for determining the 

number of landings for parts without a part 

number or serial number on which the time 

since new (TSN) and cycles since new (CSN) 

have not been tracked.

TABLE 2.—MESSIER-DOWTY SERVICE BULLETINS

Messier-Dowty service bulletin Model Landing gear corresponding Component Bombardier 

service bulletin(s) 

M–DT SB104467009/010–32–1, 

dated March 19, 2001.

CL–600–1A11 (CL–600), CL–600–

2A12 (CL–601) and CL–600–

2B16 (CL–601–3A and CL–601–

3R) airplanes.

MLG side strut retraction actuator 

eye bolt.

600–0710 and 601–0546. 

M–DT SB19090–32–4, dated March 

19, 2001.

CL–600–2B16 (CL–604) airplanes .. MLG shock strut .............................. 604–32–014. 

M–DT SB20020–32–5, dated July 12, 

2001.

CL–600–2B16 (CL–604) airplanes .. NLG shock strut ............................... 604–32–014. 

M–DT SB200814001–32–3, dated 

March 19, 2001.

CL–600–1A11 (CL–600), CL–600–

2A12 (CL–601) and CL–600–

2B16 (CL–601–3A and CL–601–

3R) airplanes.

NLG drag brace hinge pin ............... 600–0710 and 601–0546. 

M–DT SB200922001/2–32–6, dated 

March 19, 2001.

CL–600–1A11 (CL–600) airplanes .. MLG shock strut .............................. 600–0710. 

M–DT SB200924003/004–32–16, 

dated July 12, 2001.

CL–600–1A11 (CL–600) airplanes .. NLG shock strut ............................... 600–0710. 

M–DT SB6100–32–10, dated March 

19, 2001.

CL–600–2A12 (CL–601) and CL–

600–2B16 (CL–601–3A and CL–

601–3R) airplanes.

MLG shock strut pin ........................ 601–0546. 

M–DT SB6500–32–1, dated March 

19, 2001.

CL–600–1A11 (CL–600), CL–600–

2A12 (CL–601) and CL–600–

2B16 (CL–601–3A and CL–601–

3R) airplanes.

MLG side strut retraction actuator ... 600–0710 and 601–0546. 

Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations 43035

TABLE 2.—MESSIER-DOWTY SERVICE BULLETINS—Continued

Messier-Dowty service bulletin Model Landing gear corresponding Component Bombardier 

service bulletin(s) 

M–DT SB7200–32–6, dated March 

19, 2001.

CL–600–1A11 (CL–600), CL–600–

2A12 (CL–601) and CL–600–

2B16 (CL–601–3A and CL–601–

3R) airplanes.

NLG drag brace hinge pin ............... 600–0710 and 601–0546. 

M–DT SB7300–32–16, dated July 12, 

2001.

CL–600–2A12 (CL–601) and CL–

600–2B16 (CL–601–3A and CL–

601–3R) airplanes.

NLG shock strut ............................... 601–0546. 

Establish the Number of Landings 

(g) At the applicable time specified in 

paragraph (f) of this AD: If a component does 

not have a serial number and the CSN or TSN 

were not tracked, use the formula in the 

applicable Messier-Dowty service bulletin in 

Table 2 of this AD to establish the number 

of landings (TSN or CSN), and record the 

newly calculated TSN or CSN in the aircraft 

log books. 

Revise the Airworthiness Limitations 

Section (ALS) 

(h) Within 30 days after the effective date 

of this AD, revise the ALS of the applicable 

Instructions for Continued Airworthiness to 

reflect the new life limits of the landing gear 

parts by inserting copies of the Canadair 

temporary revisions (TR) in Table 3 of this 

AD into the ALS of the applicable Canadair 

Time-Limits/Maintenance Check Manual. 

When the contents of the TRs are included 

in the general revisions of the ALS, these TRs 

may be removed provided the relevant 

information in the ALS is identical to that in 

the TRs.

TABLE 3.—CANADAIR TEMPORARY REVISIONS

Temporary revision 

Applicable 

Canadair timelimits/maintenance check 

manual 

Manual

section Model 

5–116, dated April 11, 2002 .......................................... PSP 605 ........... 5–10–10 CL–600–1A11 (CL–600) airplanes. 

5–190, dated April 11, 2002 .......................................... PSP 601–5 ....... 5–10–10 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

5–191, dated April 11, 2002 .......................................... PSP 601–5 ....... 5–10–11 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

5–192, dated April 11, 2002 .......................................... PSP 601–5 ....... 5–10–12 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

5–2–6, dated April 11, 2002 .......................................... CL–604 ............. 5–10–10 CL–600–2B16 (CL–604) airplanes. 

5–204, dated April 11, 2002 .......................................... PSP 601A–5 ..... 5–10–10 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

5–205, dated April 11, 2002 .......................................... PSP 601A–5 ..... 5–10–11 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

5–206, dated April 11, 2002 .......................................... PSP 601A–5 ..... 5–10–12 CL–600–2A12 (CL–601) and CL–600–2B16 (CL–

601–3A and CL–601–3R) airplanes. 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install on any airplane a landing 

gear part, unless it has had the applicable 

part number or serial number added in 

accordance with paragraph (f) of this AD; and 

had the number of landings established in 

accordance with paragraph (g) of this AD. 

No Reporting Required 

(j) Although the service bulletins identified 

in paragraph (f) of this AD specify that 

operators submit incorporation notices to 

Bombardier after each new part number or 

serial number and landings assigned to these 

parts is added, this AD does not include that 

action.

Actions Done in Accordance With Previous 

Issues of Service Bulletins 

(k) Actions done before the effective date 

of this AD in accordance with Bombardier 

Service Bulletin 601–0546, dated May 31, 

2002; and Bombardier Service Bulletin 600–

0710, dated May 31, 2002; are acceptable for 

compliance with the corresponding actions 

specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(l) The Manager, New York Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(m) Canadian airworthiness directives CF–

2003–18R1, dated January 17, 2005; CF–

2003–20, dated July 24, 2003; and CF–2003–

21R1, dated January 21, 2005; also address 

the subject of this AD. 

Material Incorporated by Reference 

(n) You must use the service information 

identified in Tables 4, 5, and 6 of this AD 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.

43036 Federal Register / Vol. 70, No. 142 / Tuesday, July 26, 2005 / Rules and Regulations 

TABLE 4.—BOMBARDIER SERVICE BULLETINS INCORPORATED BY REFERENCE

Bombardier Service Bulletins (including the Component Time Tracking Log Card and Attachments Listed 

in Table 5 of this AD) 

Revision 

level Date 

600–0710 ......................................................................................................................................................... 01 ............ December 15, 2003. 

601–0546 ......................................................................................................................................................... 01 ............ December 15, 2003. 

604–32–014 ..................................................................................................................................................... Original .... May 31, 2002. 

TABLE 5.—MESSIER-DOWTY SERVICE BULLETINS INCORPORATED BY REFERENCE

Messier-Dowty Service Bulletin

(attachments) Date 

Attached to Bombardier Service Bulletin(s)—

M–DT SB104467009/010–32–1 ............................................................................................................ March 19, 2001 ...... 600–0710, 601–0546 

M–DT SB19090–32–4 ........................................................................................................................... March 19, 2001 ...... 604–32–014 

M–DT SB20020–32–5 ........................................................................................................................... July 12, 2001 ......... 604–32–014 

M–DT SB200814001–32–3 ................................................................................................................... March 19, 2001 ...... 600–0710, 601–0546 

M–DT SB200922001/2–32–6 ................................................................................................................ March 19, 2001 ..... 600–0710 

M–DT SB200924003/004–32–16 .......................................................................................................... July 12, 2001 ......... 600–0710 

M–DT SB6100–32–10 ........................................................................................................................... March 19, 2001 ...... 601–0546 

M–DT SB6500–32–1 ............................................................................................................................. March 19, 2001 ...... 600–0710, 601–0546 

M–DT SB7200–32–6 ............................................................................................................................. March 19, 2001 ...... 600–0710, 601–0546 

M–DT SB7300–32–16 ........................................................................................................................... July 12, 2001 ......... 601–0546 

TABLE 6.—CANADAIR TEMPORARY REVISIONS INCORPORATED BY REFERENCE

Canadair temporary revision Date 

Applicable Canadair 

time-limits/maintenance check manual Manual

section 

5–116 ................................................................................................................................ April 11, 2002 ........ PSP 605 ................ 5–10–10 

5–190 ................................................................................................................................ April 11, 2002 ........ PSP 601–5 ............ 5–10–10 

5–191 ................................................................................................................................ April 11, 2002 ........ PSP 601–5 ............ 5–10–11 

5–192 ................................................................................................................................ April 11, 2002 ........ PSP 601–5 ............ 5–10–12 

5–2–6 ................................................................................................................................ April 11, 2002 ........ CL–604 .................. 5–10–10 

5–204 ................................................................................................................................ April 11, 2002 ........ PSP 601A–5 .......... 5–10–10 

5–205 ................................................................................................................................ April 11, 2002 ........ PSP 601A–5 .......... 5–10–11 

5–206 ................................................................................................................................ April 11, 2002 ........ PSP 601A–5 .......... 5–10–12 

Issued in Renton, Washington, on July 11, 

2005. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service.

[FR Doc. 05–14175 Filed 7–25–05; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. 2002–NE–40–AD; Amendment 

39–14202; AD 2005–15–13] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524 Series Turbofan 

Engines

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT).

ACTION: Final rule.

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for Rolls 

Royce plc (RR) RB211–524 series 

turbofan engines with certain part 

number (P/N) intermediate pressure (IP) 

compressor stage 5 disks installed. This 

AD requires new reduced IP compressor 

stage 5 disk cyclic limits. This AD also 

requires removing from service affected 

disks that already exceed the new 

reduced cyclic limit, and removing 

other affected disks before exceeding 

their cyclic limits, using a drawdown 

schedule. This AD results from the 

discovery of cracks in the cooling air 

hole areas of the disk front spacer arm. 

We are issuing this AD to prevent IP 

compressor stage 5 disk failure, which 

could result in uncontained engine 

failure and possible damage to the 

airplane.

DATES: This AD becomes effective 

August 30, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulations as 

of August 30, 2005.

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31 Derby, 

DE248BJ, United Kingdom; telephone 

011–44–1332–242424; fax 011–44–

1332–249936. 

You may examine the AD docket at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA. You 

may examine the service information, at 

the FAA, New England Region, Office of 

the Regional Counsel, 12 New England 

Executive Park, Burlington, MA; or at 

the National Archives and Records 

Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, 

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

federal_register/

code_of_federal_regulations/

ibr_locations.html.

FOR FURTHER INFORMATION CONTACT: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803–