63968 Federal Register / Vol. 69, No. 212 / Wednesday, November 3, 2004 / Proposed Rules 

such findings. For a repair method to be 

approved by the Manager, Seattle ACO, as 

required by this paragraph, the Manager’s 

approval letter must specifically reference 

this AD.

(B) Repair in accordance with Part 3 of the 

Accomplishment Instructions of the alert 

service bulletin; except where the service 

bulletin specifies to contact Boeing for 

appropriate action, before further flight, 

repair in accordance with paragraph 

(h)(1)(ii)(A) of this AD. 

(2) Gain access to the upper deck floor 

beams from below the upper deck floor; and 

perform a surface HFEC inspection to detect 

cracking of the floor beams at BS 340 and 

360, and on both the left and right sides of 

the floor beam at BS 380 between BL 40 and 

76; in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2431, Revision 2, 

dated June 13, 2002. 

(i) If no cracking is found, repeat the 

inspection required by paragraph (h)(2) of 

this AD thereafter at intervals not to exceed 

750 flight cycles. 

(ii) If any cracking is found, before further 

flight, do the action specified in paragraph 

(h)(1)(ii) of this AD. 

New Post-Repair Inspection 

(i) For areas repaired in accordance with 

paragraph (h)(1)(i)(C) or (h)(1)(ii)(B) of this 

AD: Before the accumulation of the 

applicable threshold specified in the ‘‘New 

Inspection Threshold’’ column in Table 1 of 

Part 3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2431, 

Revision 2, dated June 13, 2002, after 

accomplishing the repair; or within 1,000 

flight cycles after the effective date of this 

AD; whichever occurs later: Do the actions 

specified in paragraphs (i)(1) through (i)(3) of 

this AD, as applicable. 

(1) For locations that have been repaired by 

oversizing the fastener holes only (i.e., repair 

strap and/or clip not installed) as shown in 

Part 3 of the Accomplishment Instructions of 

Revision 1 or 2 of the alert service bulletin: 

Perform an open-hole HFEC inspection to 

detect cracking of the upper deck floor 

beams, in accordance with Part 1 of the 

Accomplishment Instructions of the alert 

service bulletin. 

(2) For locations previously repaired as 

shown in Figure 8 of Revision 1 or 2 of the 

alert service bulletin: Do an open-hole HFEC 

inspection to detect cracks at the fastener 

holes of the floor panel attachment and the 

inboard and outboard end fastener locations 

common to the repair strap, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2431, Revision 2, dated June 13, 

2002. 

(3) For locations previously repaired as 

shown in Figure 9 or Figure 10 of Revision 

1 or 2 of the alert service bulletin: Do a 

surface HFEC inspection to detect cracks at 

the upper chord along the edge of the 

trimmed surface; and perform an open-hole 

HFEC inspection to detect cracks at the 

fastener holes of the floor panel attachment 

and the inboard and outboard end fastener 

locations common to the repair strap, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2431, Revision 2, 

dated June 13, 2002. 

(j) If no crack is detected during any 

inspection required by paragraphs (i)(1) 

through (i)(3) of this AD, repeat the 

applicable inspection thereafter at intervals 

not to exceed 3,000 flight cycles. 

(k) If any crack is detected during any 

inspection required by paragraph (i)(1) 

through (i)(3) of this AD, before further flight, 

do the action specified in paragraph 

(h)(1)(ii)(A) of this AD. 

(l) For areas repaired in accordance with 

paragraph (h)(1)(ii)(A) of this AD that do not 

have a post-repair inspection program 

approved by the Manager, Seattle ACO or by 

a Boeing Company DER who has been 

authorized by the Manager, Seattle ACO, to 

make those findings: Do the actions specified 

in paragraph (h) of this AD at the time 

specified in that paragraph. 

Credit for Previous Released Alert Service 

Bulletin 

(m) Actions accomplished before the 

effective date of this AD per Boeing Alert 

Service Bulletin 747–53A2431, dated 

February 10, 2000; or Revision 1, dated 

March 8, 2001; are acceptable for compliance 

with the applicable requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested in accordance with the 

procedures found in 14 CFR 39.19. 

(2) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by a 

Boeing Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make those 

findings. For a repair method to be approved, 

the approval must specifically refer to this 

AD. 

(3) AMOCs, approved previously per AD 

2000–14–17, amendment 39–11600, are 

approved as AMOCs with paragraph 

(h)(1)(ii)(A) of this AD, provided that a postrepair inspection program has been approved 

by the Manager, Seattle ACO, or by a Boeing 

Company Designated Engineering 

Representative who has been authorized by 

the Manager, Seattle ACO, to make those 

findings.

Issued in Renton, Washington, on October 

21, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24544 Filed 11–2–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 39

[Docket No. FAA–2004–19496; Directorate 

Identifier 2003–NM–181–AD] 

RIN 2120–AA64

Airworthiness Directives; Bombardier 

Model CL–215–6B11 (CL215T Variant) 

and CL–215–6B11 (CL415 Variant) 

Series Airplanes

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Bombardier Model CL–215–

6B11 (CL215T variant) and CL–215–

6B11 (CL415 variant) series airplanes. 

This proposed AD would require 

replacing the mounting pad studs of the 

auxiliary feather pump with new, longer 

studs, and installing a pressure relief 

valve. This proposed AD is prompted by 

a few incidents of external oil leaks 

from the oil pump of the power control 

unit due to a malfunction of the 

pressure regulating valve. We are 

proposing this AD to prevent fracturing 

of the pump body, which could result 

in loss of engine oil, and consequent 

inability to maintain engine oil pressure 

and to feather the propeller.

DATES: We must receive comments on 

this proposed AD by December 3, 2004.

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD. 

• DOT Docket Web site: Go to http:/

/dms.dot.gov and follow the instructions 

for sending your comments 

electronically. 

• Government-wide rulemaking Web 

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

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

room PL–401, Washington, DC 20590. 

• By fax: (202) 493–2251. 

• Hand Delivery: room PL–401 on the 

plaza level of the Nassif Building, 400 

Seventh Street, SW., Washington, DC, 

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

through Friday, except Federal holidays. 

You can get the service information 

identified in this proposed AD from 

Bombardier, Inc., Canadair, Aerospace 

Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9, 

Canada. 

You may examine the contents of this 

AD docket on the Internet at http://

Federal Register / Vol. 69, No. 212 / Wednesday, November 3, 2004 / Proposed Rules 63969

dms.dot.gov, or at the Docket 

Management Facility, U.S. Department 

of Transportation, 400 Seventh Street, 

SW., room PL–401, on the plaza level of 

the Nassif Building, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Richard Fiesel, Aerospace Engineer, 

Airframe and Propulsion Branch, ANE–

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Westbury, suite 410, New York 

11590; telephone (516) 228–7304; fax 

(516) 794–5531.

SUPPLEMENTARY INFORMATION:

Docket Management System (DMS) 

The FAA has implemented new 

procedures for maintaining AD dockets 

electronically. As of May 17, 2004, new 

AD actions are posted on DMS and 

assigned a docket number. We track 

each action and assign a corresponding 

directorate identifier. The DMS AD 

docket number is in the form ‘‘Docket 

No. FAA–2004–99999.’’ The Transport 

Airplane Directorate identifier is in the 

form ‘‘Directorate Identifier 2004–NM–

999–AD.’’ Each DMS AD docket also 

lists the directorate identifier (‘‘Old 

Docket Number’’) as a cross-reference 

for searching purposes. 

Comments Invited 

We invite you to submit any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2004–19496; Directorate Identifier 

2003–NM–181–AD ‘‘at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments submitted by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http://

dms.dot.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of our docket 

Web site, anyone can find and read the 

comments in any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). You may 

review the DOT’s complete Privacy Act 

Statement in the Federal Register

published on April 11, 2000 (65 FR 

19477–78), or you may visit http://

dms.dot.gov.

We are reviewing the writing style we 

currently use in regulatory documents. 

We are interested in your comments on 

whether the style of this document is 

clear, and your suggestions to improve 

the clarity of our communications that 

affect you. You can get more 

information about plain language at 

http://www.faa.gov/language and http://

www.plainlanguage.gov.

Examining the Docket 

You may examine the AD docket 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 DOT 

street address stated in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after the DMS 

receives them. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the airworthiness 

authority for Canada, notified us that an 

unsafe condition may exist on certain 

Bombardier Model CL–215–6B11 

(CL215T variant) and CL–215–6B11 

(CL415 variant) series airplanes. The 

TCCA advises that there have been a 

few incidents of external oil leaks from 

the oil pump of the propeller control 

unit due to a malfunction of the 

pressure regulating valve, on Pratt & 

Whitney Model PW120 series engines. 

The resulting high internal oil pressure 

may cause a fracture of the pump body. 

This condition, if not corrected, could 

result in loss of engine oil, and 

consequent inability to maintain engine 

oil pressure and to feather the propeller. 

Relevant Service Information 

Bombardier has issued Service 

Bulletin 215–3108, dated March 28, 

2001 (for Model CL–215–6B11 (CL215T 

variant) series airplanes); and 

Bombardier Service Bulletin 215–4234, 

dated March 28, 2001 (for Model CL–

215–6B11 (CL415 variant) series 

airplanes). The service bulletins 

describe procedures for replacing the 

mounting pad studs of the auxiliary 

feather pump with new, longer studs, 

and installing a pressure relief valve. 

Accomplishing the actions specified in 

the service information will adequately 

address the unsafe condition. TCCA 

mandated the service information and 

issued Canadian airworthiness directive 

CF–2002–14, dated February 13, 2002, 

to ensure the continued airworthiness of 

these airplanes in Canada. 

The service bulletins refer to Pratt & 

Whitney Canada Service Bulletin 

PW100–72–21636, Revision 2, dated 

June 26, 2002, as an additional source 

of service information for doing the 

replacement of the mounting pad studs. 

FAA’s Determination and Requirements 

of the Proposed AD 

These airplane models are 

manufactured in Canada and are type 

certificated for operation in the United 

States under the provisions of section 

21.29 of the Federal Aviation 

Regulations (14 CFR 21.29) and the 

applicable bilateral airworthiness 

agreement. Pursuant to this bilateral 

airworthiness agreement, TCCA has 

kept the FAA informed of the situation 

described above. We have examined the 

TCCA’s findings, evaluated all pertinent 

information, and determined that AD 

action is necessary for products of this 

type design that are certificated for 

operation in the United States. 

Therefore, we are proposing this AD, 

which would require replacing the 

mounting pad studs of the auxiliary 

feather pump with new, longer studs, 

and installing a pressure relief valve. 

The proposed AD would require you to 

use the Bombardier service information 

described previously to perform these 

actions, except as discussed under 

‘‘Difference Between Proposed Rule and 

Referenced Service Bulletins.’’

Difference Between Proposed Rule and 

Referenced Service Bulletins 

Operators should note that, although 

the Accomplishment Instructions of the 

referenced Bombardier service bulletins 

describe procedures for submitting a 

sheet recording compliance with the 

service bulletin, this proposed AD 

would not require that action. We do 

not need this information from 

operators. 

Costs of Compliance 

The following table provides the 

estimated costs for U.S. operators to 

comply with this proposed AD.

63970 Federal Register / Vol. 69, No. 212 / Wednesday, November 3, 2004 / Proposed Rules 

ESTIMATED COSTS

Action Work 

hours 

Average labor 

rate per hour Parts Cost perairplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Replacement .................................................................... 2 $65 Free ..... $130 3 $390

Installation ........................................................................ 4 65 Free ..... 260 3 780

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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, Safety.

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 adding 

the following new airworthiness 

directive (AD):

Bombardier, Inc. (Formerly Canadair):

Docket No. FAA–2004–19496; 

Directorate Identifier 2003–NM–181–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

must receive comments on this AD action by 

December 3, 2004. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier Model 

CL–215–6B11 (CL215T variant) having serial 

numbers (S/N) 1056 through 1125 inclusive, 

and Model CL–215–6B11 (CL415 variant) 

series airplanes, having S/Ns 2001 through 

2053 inclusive; certificated in any category. 

Unsafe Condition 

(d) This AD was prompted by a few 

incidents of external oil leaks from the oil 

pump of the power control unit due to a 

malfunction of the pressure regulating valve. 

We are issuing this AD to prevent fracturing 

of the pump body, which could result in loss 

of engine oil, and consequent inability to 

maintain engine oil pressure and to feather 

the propeller. 

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. 

Replacement 

(f) Within 12 months after the effective 

date of this AD, replace the mounting pad 

studs of the auxiliary feather pump with 

new, longer studs, and install a pressure 

relief valve; in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 215–3108, dated March 28, 

2001 (for Model CL–215–6B11 (CL215T 

variant) series airplanes); or Bombardier 

Service Bulletin 215–4234, dated March 28, 

2001 (for Model CL–215–6B11 (CL415 

variant) series airplanes); as applicable.

Note 1: Bombardier Service Bulletin 215–

3108 and Bombardier Service Bulletin 215–

4234 refer to Pratt & Whitney Canada Service 

Bulletin PW100–72–21636, Revision 2, dated 

June 26, 2002, as an additional source of 

service information for accomplishing the 

replacement of the mounting pad studs.

No Reporting 

(g) Although the service bulletin refers to 

a reporting requirement in paragraph 2.B, 

that reporting is not required by 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 

using the procedures found in 14 CFR 39.19. 

Related Information 

(i) Canadian airworthiness directive CF–

2002–14, dated February 13, 2002, also 

addresses the subject of this AD.

Issued in Renton, Washington, on October 

21, 2004. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service.

[FR Doc. 04–24543 Filed 11–2–04; 8:45 am] 

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration 

14 CFR Part 71

[Docket No. FAA–2004–19362; Airspace 

Docket No. 04–AAL–22] 

Proposed Establishment of Class E 

Airspace; Red Dog, AK

AGENCY: Federal Aviation 

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This action proposes to 

establish new Class E airspace at Red 

Dog, AK. There is no existing Class E 

airspace to contain aircraft executing 

instrument approaches at Red Dog 

Airport. Adoption of this proposal 

would result in the establishment of 

Class E airspace upward from 700 feet 

(ft.) and 1,200 ft. above the surface at 

Red Dog, AK.

DATES: Comments must be received on 

or before December 20, 2004.

ADDRESSES: Send comments on the 

proposal to the Docket Management 

System, U.S. Department of 

Transportation, Room Plaza 401, 400 

Seventh Street, SW., Washington, DC 

20590–0001. You must identify the 

docket number FAA–2004–19362/

Airspace Docket No. 04–AAL–22, at the 

beginning of your comments. You may 

also submit comments on the Internet at 

http://dms.dot.gov. You may review the 

public docket containing the proposal, 

any comments received, and any final 

disposition in person in the Dockets 

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

Monday through Friday, except Federal 

holidays. The Docket Office (telephone 

1–800–647–5527) is on the plaza level 

of the Department of Transportation 

NASSIF Building at the above address. 

An informal docket may also be 

examined during normal business hours 

at the office of the Manager, Safety,