Federal Register / Vol. 65, No. 198 / Thursday, October 12, 2000 / Proposed Rules 60595

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

39 of the Federal Aviation Regulations

(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. Section 39.13 is amended by

adding the following new airworthiness

directive:

Gulfstream Aerospace Corporation: Docket

2000–NM–144–AD.

Applicability: Model G–1159A (G–III)

series airplanes, serial numbers 357 and 402

through 498 inclusive, certificated in any

category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the flight crew from being

unaware that an electrical system failure has

occurred and that the airplane main batteries

are powering the direct current (DC) essential

bus, accomplish the following:

(a) Within 12 months after the effective

date of this AD, modify the wiring in the

pilot’s and co-pilot’s junction boxes, the

auxiliary power relay box, the power

distribution box, and the master caution

panel, in accordance with Gulfstream

Customer Bulletin No. 149, dated March 23,

1999, and Gulfstream Aircraft Service Change

No. 294, dated February 3, 1999.

Alternative Methods of Compliance

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, Atlanta

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on October

4, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26094 Filed 10–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–181–AD]

RIN 2120–AA64

Airworthiness Directives; Bombardier

Model DHC–7–100, –101, –102, and

–103 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Bombardier Model DHC–7–100,

–101, –102, and –103 series airplanes.

This proposal would require inspecting

the endcaps of the main landing gear

selector valve for leaks of hydraulic oil

and, if leaks are detected, replacing the

leaking endcaps or the entire selector

valve. This proposal would also require

eventual replacement or rework of

certain selector valves, which would

terminate the repetitive inspections.

This action is prompted by a report of

the collapse of the main landing gear

due to an external leak of hydraulic oil

in the landing gear selector valve,

resulting from a fracture of the endcap.

This action is intended to prevent leaks

of hydraulic oil from the main landing

gear selector valve, which could result

in the collapse of the main landing gear.

DATES: Comments must be received by

November 13, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

181–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9–anm–

nprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–181–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

The service information referenced in

the proposed rule may be obtained from

Bombardier, Inc., Canadair, Aerospace

Group, P.O. Box 6087, Station

Centreville, Montreal, Quebec H3C 3G9,

Canada. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York.

FOR FURTHER INFORMATION CONTACT:

James E. Delisio, Aerospace Engineer,

ANE–171, FAA, New York Aircraft

Certification Office, 10 Fifth Street,

Third Floor, Valley Stream, New York

11581; telephone (516) 256–7521; fax

(516) 568–2716.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Submit comments using the following

format:

• Organize comments issue-by-issue.

For example, discuss a request to

change the compliance time and a

request to change the service bulletin

reference as two separate issues.

• For each issue, state what specific

change to the proposed AD is being

requested.

• Include justification (e.g., reasons or

data) for each request.

Comments are specifically invited on

the overall regulatory, economic,

60596 Federal Register / Vol. 65, No. 198 / Thursday, October 12, 2000 / Proposed Rules

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 2000–NM–181–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

2000–NM–181–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

Transport Canada Civil Aviation

(TCCA), which is the airworthiness

authority for Canada, notified the FAA

that an unsafe condition may exist on

certain Bombardier Model DHC–7–100,

–101, –102, and –103 series airplanes.

TCCA advises that an investigation of

the collapse of the main landing gear of

a Model DHC–8 series airplane

identified the cause as an external

hydraulic oil leak in the landing gear

selector valve due to a fracture of the

endcap. Model DHC–7 series airplanes

have the same parts in their main

landing gears.

TCCA further advises that inspection

of main landing gear selector valves

undergoing bench testing have revealed

additional cases of fatigue failure in the

endcaps. In addition, main landing gear

selector valves which have not been

upgraded to part number (P/N) 57420–

5 configuration are more susceptible to

internal leaks, and excessive internal

leaks can also contribute to the collapse

of the main landing gear. This

condition, if not corrected, could result

in leaks of hydraulic oil from the main

landing gear selector valve, which could

result in the collapse of the main

landing gear.

Explanation of Relevant Service

Information

Bombardier has issued Alert Service

Bulletin A7–32–103, dated September 3,

1999, which describes procedures for

repetitive visual inspection of the

endcaps of the main landing gear

selector valve for leaks of hydraulic oil

and replacement of the endcaps with

new serviceable parts, if leaks are found.

The service bulletin also describes

procedures for rework or replacement of

certain selector valves with new

improved parts, which would eliminate

the need for the repetitive inspections.

Accomplishment of the actions

specified in the service bulletin is

intended to adequately address the

identified unsafe condition. TCCA

classified this service bulletin as

mandatory and issued Canadian

airworthiness directive CF–99–31, dated

December 21, 1999, in order to assure

the continued airworthiness of these

airplanes in Canada.

FAA’s Conclusions

These airplane models are

manufactured in Canada and are type

certificated for operation in the United

States under the provisions of § 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. The FAA has

examined the findings of TCCA,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletin described

previously. The FAA is also preparing a

proposed AD, which will address a

similar unsafe condition on Bombardier

Model DHC–8–100, –200, and –300

series airplanes.

Cost Impact

The FAA estimates that 32 airplanes

of U.S. registry would be affected by this

proposed AD, that it would require 1

work hour per airplane to accomplish

the proposed inspection, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the proposed inspection on U.S.

operators is estimated to be $1,920, or

$60 per airplane.

The FAA also estimates that it would

require 5 work hours per airplane to

rework or replace the main landing gear

selector valve and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the

proposed rework or replacement on U.S.

operators is estimated to be $9,600 or

$300 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this proposed AD were not adopted. The

cost impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

Should an operator elect to replace

the endcaps and perform the optional

repetitive inspections prior to replacing

the main landing gear selector valve, it

would take approximately 1 work hour

per airplane to conduct each inspection.

Based on these figures, the cost impact

of the optional repetitive inspections is

estimated to be $60 per inspection per

airplane.

Regulatory Impact

The regulations proposed herein

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. Therefore,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

For the reasons discussed above, I

certify that this 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) if

promulgated, 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. A copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend part

Federal Register / Vol. 65, No. 198 / Thursday, October 12, 2000 / Proposed Rules 60597

39 of the Federal Aviation Regulations

(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. Section 39.13 is amended by

adding the following new airworthiness

directive:

Bombardier, Inc. (Formerly de Havilland,

Inc.): Docket 2000–NM–181–AD.

Applicability: Model DHC–7–100, –101,

–102, and –103 series airplanes, serial

numbers 003 through 113 inclusive;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

modified, altered, or repaired in the area

subject to the requirements of this AD. For

airplanes that have been modified, altered, or

repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent the collapse of the main

landing gear due to leaks of hydraulic oil

from the main landing gear selector valve,

accomplish the following:

Inspection

(a) Within 100 flight cycles after the

effective date of this AD, perform a general

visual inspection of both endcaps of the main

landing gear selector valve for the presence

of hydraulic oil, in accordance with the

Accomplishment Instructions of Bombardier

Alert Service Bulletin A7–32–103, dated

September 3, 1999. If no hydraulic oil is

detected on either endcap, repeat the

inspection at intervals not to exceed 400

flight hours until the requirements of

paragraph (c) are accomplished.

Note 2: For the purposes of this AD, a

general visual inspection is defined as: ‘‘A

visual examination of an interior or exterior

area, installation, or assembly to detect

obvious damage, failure, or irregularity. This

level of inspection is made under normally

available lighting conditions such as

daylight, hangar lighting, flashlight, or droplight, and may require removal or opening of

access panels or doors. Stands, ladders, or

platforms may be required to gain proximity

to the area being checked.’’

Replacement or Modification

(b) If any hydraulic oil is detected on either

endcap: Prior to further flight, perform the

actions specified in either paragraph (b)(1) or

(b)(2) of this AD.

(1) Replace the existing aluminum

endcaps, part number (P/N) 34629, with new

stainless steel endcaps having P/N 52982, in

accordance with the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A7–32–103, dated September 3,

1999.

(2) Replace the main landing gear selector

valve with a valve having P/N 57420–5A, in

accordance with the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A7–32–103, dated September 3,

1999.

Note 3: Use care when removing the

endcaps, so that the internal components do

not fall on the ground and get damaged.

(c) Within 12 months after the effective

date of this AD: Perform the actions specified

in either paragraph (c)(1) or (c)(2) of this AD,

in accordance with the Accomplishment

Instructions of Bombardier Alert Service

Bulletin A7–32–103, dated September 3,

1999. Accomplishment of either paragraph

(c)(1) or (c)(2) terminates the repetitive

inspection requirement of this AD.

(1) If a main landing gear selector valve

having P/N 57420–1 or 57420–3 is installed,

remove it and replace it with a valve having

P/N 57420–5A.

(2) If a main landing gear selector valve

having P/N 57420–5 is installed, remove it

and replace it with a valve having P/N

57420–5A or modify the valve to the P/N

57420–5A configuration (Modification 7/

2742).

Alternative Methods of Compliance

(d) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager, New York

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, New York ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York ACO.

Special Flight Permits

(e) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the airplane to a

location where the requirements of this AD

can be accomplished.

Note 5: The subject of this AD is addressed

in Canadian airworthiness directive CF–99–

31, dated December 21, 1999.

Issued in Renton, Washington, on October

4, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–26093 Filed 10–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 90–ANE–25–AD; Amendment

No. 39–XXXXX]

RIN 2120–AA64

Airworthiness Directives; General

Electric Company (GE) CF–645 and

CF6–50 Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

revise an existing airworthiness

directive (AD), applicable to certain GE

turbofan engines. That AD currently

requires initial and repetitive

inspections of high pressure compressor

(HPC) rear shafts and installation of a

certain rear shaft flange bolt

configuration. This action would add

additional HPC rear shaft part numbers

for reworked rear shafts to the AD. This

proposal is prompted by the need to

ensure that the additional HPC rear

shafts listed in this proposed rule

receive the same inspections as part

numbers covered by the current

amendment. The actions specified by

the proposed AD are intended to detect

and replace cracked HPC rear shafts,

which, if not replaced, could lead to an

uncontained engine failure.

DATES: Comments must be received by

November 16, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 90–ANE–25–AD, 12 New

England Executive Park, Burlington, MA

01803–5299. Comments may also be

sent via the Internet using the following

address: ‘‘9-ane-adcomment@faa.gov’’.

Comments sent via the Internet must

contain the docket number in the

subject line. Comments may be

inspected at this location between 8:00

a.m. and 4:30 p.m., Monday through

Friday, except Federal holidays. The

service information referenced in the

proposed rule may be obtained from

General Electric Company, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington MA; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700,

Washington, DC.