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.

60598 Federal Register / Vol. 65, No. 198 / Thursday, October 12, 2000 / Proposed Rules

FOR FURTHER INFORMATION CONTACT:

Karen Curtis, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone: (781) 238–7192;

fax: (781) 238-7199.

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

should identify the Rules Docket

number and be submitted 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.

Comments are specifically invited on

the overall regulatory, economic,

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 Number 90–ANE–25–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRM’s

Any person may obtain a copy of this

NPRM by submitting a request to the

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.

Discussion

On March 18, 1991, the FAA issued

AD 91–10–03, Amendment 39–6956 (56

FR 19920, May 1, 1991), applicable to

GE CF6–45 and CF6–50 turbofan

engines, to require initial and repetitive

inspections of HPC rear shafts and

installation of a certain rear shaft flange

bolt. That action was prompted by

reports of 35 HPC rear shafts found

cracked in the bolt hole area. The

inspection requirements of that AD were

intended to detect and replace cracked

HPC rear shafts to prevent an HPC rear

shaft fracture, which could result in an

uncontained engine failure. On April 4,

1995, the FAA issued AD 91–10–03

Revision 1, Amendment 39–9186 (60 FR

1879, May 13, 1995), applicable to GE

CF6–45 and CF6–50 series turbofan

engines. That action was prompted by

an FAA determination that the Parts

Manufacturer Approval (PMA)

Production Approval Listing,

Supplement No. 27, authorizes the use

of Valley-Todeco (VT) bolts, part

number (P/N) VCD0016, as an alternate

to GE bolts, P/N 1375M69P01. The VT

bolt is identical in design to the GE bolt

and the amendment adds the VT bolt to

the applicability. That amendment also

clarifies that engines with one or more

PMA bolts, P/N VCD0016 installed,

must accomplish the inspection

requirements of the original AD, and

allow the installation of PMA bolts as

alternates to the GE bolts. That AD

Revision requires initial and repetitive

inspections to detect and replace

cracked HPC rear shafts to prevent an

HPC rear shaft fracture, which could

result in an uncontained engine failure.

New Information

Since that revision to the AD was

issued, the FAA has become aware of

HPC rear shaft rework P/N’s that have

been issued by the manufacturer that are

not listed in AD 91–10–03, Revision 1

but should be inspected.

Proposed Actions

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

revise AD 91–10–03 Revision 1 to add

HPC rear shaft rework P/N’s to the AD.

The actions would be required to be

accomplished in accordance with the

SB’s described previously.

Economic Impact

There are about 1,730 engines of the

affected design in the worldwide fleet.

The FAA estimates that 469 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take about 2 work hours

per engine to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required labor

would cost about $120.00 per engine.

Based on these figures, the total labor

cost impact of the proposed AD on U.S.

operators is estimated to be $56,280.

Regulatory Impact

This proposal does not have

federalism implications, as defined in

Executive Order 13132, because it

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.

Accordingly, the FAA has not consulted

with state authorities prior to

publication of this proposal.

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

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

removing Amendment 39–9186 (60 FR

18729, April 13, 1995), and by adding

a new airworthiness directive (AD), to

read as follows:

General Electric Company: Docket No. 90–

ANE–25–AD. Revises AD 91–10–03,

Revision 1, Amendment 39–9186.

Applicability: General Electric Company

(GE) CF6–45 and CF6–50 series turbofan

engines installed on, but not limited to,

McDonnell Douglas DC–10 series, Boeing 747

series, and Airbus A300 series airplanes.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 (e)

Federal Register / Vol. 65, No. 198 / Thursday, October 12, 2000 / Proposed Rules 60599

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 a high

pressure compressor (HPC) rear shaft

fracture, which could result in an

uncontained engine failure and/or in-flight

engine shutdown, accomplish the following:

(a) Fluorescent-penetrant inspect HPC rear

shafts having the part numbers (P/N’s) in

Table 1 below, in accordance with the

Accomplishment Instructions of GE Service

Bulletin (SB) No. 72–958, Revision 1, dated

October 18, 1990 as follows:

TABLE 1

9127M58P03 9079M63P12 9079M63P15 9079M63P16

9079M63P17 9079M63P18 9079M63P19 1999M25P01

1999M25P02 1999M25P03 1999M25P04 1999M25P05

1999M25P06 1999M25P07

(1) For HPC rear shafts currently installed

with hook bolts, P/N 9012M99G10,

9114M95G07, and 9114M95G10, inspect in

accordance with the following schedule:

(i) For shafts that have not been previously

inspected and have 10,000 cycles since new

(CSN) or more on the effective date of this

AD, inspect within the next 1,500 cycles in

service (CIS) after the effective date of this

AD.

(ii) For shafts that have not been previously

inspected and have fewer than 10,000 CSN

on the effective date of this AD, inspect

within the next 2,500 CIS from the effective

date of this AD, or before accumulating 7,500

CSN, whichever occurs later. However, no

shaft may exceed 11,500 CSN before

inspection.

(iii) For shafts that have been previously

inspected and have 3,000 cycles since last

inspection (CSLI) or fewer on the effective

date of this AD, inspect within 4,500 CSLI,

or before accumulating 7,500 CSN,

whichever occurs later.

(iv) For shafts that have been previously

inspected and have greater than 3,000 CSLI

on the effective date of this AD, inspect

within the next 1,500 CIS from the effective

date of this AD, or before accumulating 7,500

CSN, whichever occurs later.

(v) Remove from service HPC rear shaft

hook bolts identified in (a)(1) of this AD after

any inspection performed in accordance with

paragraph (a)(1) of this AD and replace with

new tapered turn-around bolts, P/N

1375M69P01 or VCD0016.

(2) For HPC rear shafts installed with turnaround bolts, P/N 9249M54P01, or tapered

turn-around bolts, P/N 1375M69P01 or

VCD0016, inspect in accordance with the

following schedule:

(i) For shafts that have not been previously

inspected and have 6,500 CSN or more on the

effective date of this AD, inspect within the

next 2,500 CIS after the effective date of this

AD.

(ii) For shafts that have not been previously

inspected and have fewer than 6,500 CSN on

the effective date of this AD, inspect before

accumulating 9,000 CSN.

(iii) For shafts that have been previously

inspected and have 3,500 CSLI or fewer on

the effective date of this AD, inspect within

6,000 CSLI, or before accumulating 9,000

CSN, whichever occurs later.

(iv) For shafts that have been previously

inspected and have more than 3,500 CSLI on

the effective date of this AD, inspect within

the next 2,500 CIS after the effective date of

this AD, or before accumulating 9,000 CSN,

whichever occurs later.

(v) Remove from service HPC rear shaft

turn-around bolts identified in paragraph

(a)(2) of this AD after any inspection

performed in accordance with paragraph

(a)(3) of this AD and replace with new

tapered turn-around bolts, P/N 1375M69P01

or VCD0016.

Note 2. Information concerning the tapered

turn-around bolt noted in paragraph (a) of

this proposed AD can be found in GE SB No.

72–877.

(b) Remove from service, prior to further

flight, any shafts found cracked at inspection.

(c) Thereafter, for shafts that have been

inspected in accordance with paragraph (a) of

this AD, reinspect in accordance with the

Accomplishment Instructions of GE SB No.

72–958, Revision 1, dated October 18, 1990,

at intervals not to exceed 6,000 CSLI.

(d) Compliance with paragraph (a) of AD

91–10–03, Revision 1 satisfies the

corresponding requirements of paragraph (a)

of this AD. For the purposes of this AD, the

inspection cycle interval must be measured

from the last HPC rear shaft bolt hole

inspection, regardless of any rear shaft

rework and re-identifying after inspection.

Alternative Methods of Compliance

(e) 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, Engine

Certification Office (ECO). Operators shall

submit their request through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Manager,

ECO.

Special Flight Permits

(f) 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 aircraft to a

location where the requirements of this AD

can be accomplished.

Issued in Burlington, Massachusetts, on

October 5, 2000.

David A. Downey,

Assistant Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–26141 Filed 10–11–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–CE–74–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Beech Models 60,

A60, and B60 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Raytheon Aircraft Company (Raytheon)

Beech Models 60, A60, and B60

airplanes. The proposed AD would

require you to inspect for the existence

of any lower forward wing bolts with

the Mercury Aerospace trademark, and

replace any such bolt with an

FAAapproved bolt without this

trademark. The proposed AD is the

result of a report that wing bolts

supplied by Mercury Aerospace may not

meet the required Rockwell hardness

specifications. The actions specified by

the proposed AD are intended to detect

and correct wing bolts that do not meet

strength requirements. Continued

airplane operation with such bolts could

result in fatigue failure of the bolts with

consequent separation of the wing from

the airplane.

DATES: The Federal Aviation

Administration (FAA) must receive any

comments on this rule on or before

December 5, 2000.