Federal Register / Vol. 65, No. 15 / Monday, January 24, 2000 / Proposed Rules 3619

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 ice accumulation on the

airplane leading edges, which could result in

reduced controllability of the airplane,

accomplish the following:

Modification

(a) Within 1 year after the effective date of

this AD, replace the pneumatic de-icing boot

pressure indicator switch with a switch that

activates the flight deck indicator light at 15

pounds per square inch gage, in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

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,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with sections 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 January 18,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1598 Filed 1–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–13–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BAe 125–800A and BAe 125–

800B, Model Hawker 800, and Model

Hawker 800XP Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Raytheon Model BAe 125–800A, Model

Hawker 800, and Model Hawker 800XP

series airplanes, that currently requires

the filling of two tooling holes on the

firewalls of the left and right engine

pylons with firewall sealant. This action

would require the sealing of all unused

(open) tooling holes on the firewalls of

the left and right engine pylons, and

would expand the applicability to

include additional airplanes. This

proposal is prompted by reports of

additional unused (open) tooling holes,

found at locations other than those

currently addressed. The actions

specified by the proposed AD are

intended to prevent an engine fire from

moving to the fuselage and to the lines

that carry flammable fluid that are

located inboard of the firewall.

DATES: Comments must be received by

February 23, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 99–NM–

13–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Raytheon Aircraft Company, Manager

Service Engineering, Hawker Customer

Support Department, P.O. Box 85,

Wichita, Kansas, 67201–0085. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small

Airplane Directorate, Wichita Aircraft

Certification Office, 1801 Airport Road,

Room 100, Mid-Continent Airport,

Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT:

Jeffrey A. Pretz, Aerospace Engineer,

Systems and Propulsion Branch, ACE–

116W, FAA, Small Airplane Directorate,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas

67209; telephone (316) 946–4153; fax

(316) 946–4407.

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.

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 99–NM–13–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.

99–NM–13–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On November 22, 1996, the FAA

issued AD 96–24–16, amendment 39–

9840 (61 FR 66878, December 19, 1996),

applicable to certain Raytheon Model

BAe 125–800A, Model Hawker 800, and

Model Hawker 800XP series airplanes,

to require the filling of two tooling holes

on the firewalls of the left and right

engine pylons with firewall sealant.

That action was prompted by

notification from the manufacturer that

these holes were not sealed during

production. The requirements of that

AD are intended to prevent an engine

fire from moving to the fuselage and to

the lines that carry flammable fluid that

are located inboard of the firewall.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, reports

have been received of airplanes with

additional unused tooling holes, at

locations other than those addressed in

AD 96–24–16, on the left and right

engine pylon firewalls, which may

permit the passage of flames to the

3620 Federal Register / Vol. 65, No. 15 / Monday, January 24, 2000 / Proposed Rules

structure and flammable fluids inboard

of the engine pylon firewall.

Explanation of Relevant Service

Information

Raytheon has issued Service Bulletin

SB.54–1–3815B, Revision 1, dated May

1998, which describes procedures for

the sealing of all unused tooling holes

on the firewalls of the left and right

engine pylons. Revision 1 of the service

bulletin was issued to address

additional unused engine pylon firewall

tooling holes at locations other than

those indicated in the original service

bulletin, dated March 26, 1996.

Accomplishment of the actions

specified in Raytheon Service Bulletin

SB.54–1–3815B, Revision 1, is intended

to adequately address the identified

unsafe condition.

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, the proposed AD would

supersede AD 96–24–16 to require the

sealing of all unused tooling holes on

the firewalls of the left and right engine

pylons. The actions would be required

to be accomplished in accordance with

Raytheon Service Bulletin SB.54–1–

3815B, Revision 1, described

previously.

Expanded Applicability

The applicability of the proposed AD

has been expanded to include Model

BAe 125–800B series airplanes, which

have received FAA type certification

and have a similar design to airplanes

subject to the requirements of AD 96–

24–16.

Cost Impact

There are approximately 340 Model

BAe 125–800A and BAe 125–800B,

Model Hawker 800, and Model Hawker

800XP series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 221 airplanes of U.S.

registry would be affected by this

proposed AD.

The actions that are currently

required by AD 96–24–16, and retained

in this AD, take approximately 2 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the currently required actions on U.S.

operators is estimated to be $120 per

airplane.

The new actions that are proposed in

this AD action would take

approximately 2 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

proposed requirements of this AD on

U.S. operators is estimated to be

$26,520, or $120 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or proposed requirements of

this AD action, and that no operator

would accomplish those actions in the

future if this AD were not adopted.

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

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 39–9840 (61 FR

66878, December 19, 1996), and by

adding a new airworthiness directive

(AD), to read as follows:

Raytheon Aircraft Co. (Formerly Beech):

Docket 99–NM–13–AD. Supersedes AD

96–24–16, Amendment 39–9840.

Applicability: Model BAe 125–800A and

BAe 125–800B, Model Hawker 800, and

Model Hawker 800XP series airplanes; as

listed in Raytheon Service Bulletin SB.54–1–

3815B, Revision 1, dated May 1998;

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 (c) 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 an engine fire from moving to

the fuselage and to the lines that carry

flammable fluid that are located inboard of

the firewall, accomplish the following:

Restatement of Requirements of AD 96–24–

16

(a) For airplanes identified in AD 96–24–

16, amendment 39–9840: Within 6 months

after January 27, 1997 (the effective date of

AD 96–24–16), fill the two, unused tooling

holes in the firewalls of the left and right

engine pylons, in accordance with Raytheon

Service Bulletin SB.54–1–3815B, dated

March 26, 1996, or Raytheon Service Bulletin

SB.54–1–3815B, Revision 1, dated May 1998.

After the effective date of this AD, only

Revision 1 of this service bulletin shall be

used.

New Requirements of This AD

(b) For all airplanes: Within 6 months after

the effective date of this AD, fill all unused

tooling holes in the left and right engine

pylon firewalls with firewall sealant, in

accordance with Raytheon Service Bulletin

SB.54–1–3815B, Revision 1, dated May 1998.

Alternative Methods of Compliance

(c) 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, Wichita

Aircraft Certification Office (ACO), ACE–

116W, FAA, Small Airplane Directorate.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permits

(d) Special flight permits may be issued in

accordance with sections §§ 21.197 and

Federal Register / Vol. 65, No. 15 / Monday, January 24, 2000 / Proposed Rules 3621

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 January

18, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1597 Filed 1–21–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NE–40–AD]

RIN 2120–AA64

Airworthiness Directives; CFM

International CFM56–2, –2A, –2B, –3,

–3B, –3C, –5, –5B, –5C Series Turbofan

Engines

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 CFM

International (CFMI) CFM56–2, –2A,

–2B, –3, –3B, –3C, –5, –5B, –5C series

turbofan engines. This proposal would

require initial and repetitive visual

inspections of the fuel pump filter cover

helicoil inserts and bolts for damage,

and, if necessary, repair or replacement

with serviceable parts. This proposal

also would require the installation of

new fuel pumps that incorporate an

improved filter cover retention design

(D-bolts) as terminating action to the

inspections. This proposal is prompted

by reports that fuel pump filter cover

helicoil inserts have loosened or pulled

out. The actions specified by the

proposed AD are intended to prevent

fuel leakage from between the fuel

pump filter cover and gear housing,

which could result in an engine fire and

damage to the airplane.

DATES: Comments must be received by

February 23, 2000.

ADDRESSES: Submit comments to the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 99–NE–40–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

CFM International, Technical

Publications Department, 1 Neumann

Way, Cincinnati, OH 45215; telephone

(513) 552–2981, fax (513) 552–2816.

This information may be examined at

the FAA, New England Region, Office of

the Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

James Rosa, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7152, 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 99-NE–40–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 99–NE–40–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports of fuel

leakage from between the fuel pump

filter cover and gear housing on CFM

International (CFMI) CFM56–2, –2A,

–2B, –3, –3B, –3C, –5, –5B, –5C series

turbofan engines.

Investigation

The investigation revealed that fuel

pump filter cover helicoil inserts have

loosened or pulled out. The FAA has

identified excessive torque during the

installation of fuel filter cover bolts as

the cause.

Improved Filter Cover

The manufacturer has introduced an

improved filter cover retention design

using a captured D-bolt and special

locking nut that reduces the potential

for filter cover bolt over torque damage

and loss of bolted joint strength.

Unsafe Condition

This condition, if not corrected, could

result in fuel leakage from between the

fuel pump filter cover and gear housing,

which could result in an engine fire and

damage to the airplane.

Service Information

The FAA has reviewed and approved

the technical contents of the following

CFMI Service Bulletins (SBs), that

describe procedures for visual

inspections of inserts and bolts for

damage, and provide criteria for

rejection of hardware and necessary

replacement with serviceable parts:

CFM56–2 SB 73–110, Revision 2, dated

April 29, 1999; CFM56

The FAA has also reviewed and

approved the technical contents of the

following CFMI SBs, that describe

procedures for removal and replacement

of fuel pumps (D-bolt fix): CFM56–2 SB

73–-A113, dated August 17, 1999;

CFM56–2A SB 73–A058, dated August

17, 1999; CFM56–2B SB 73–A079, dated

August 17, 1999; CFM56–3/3B/3C SB

73-A129, dated August 17, 1999;

CFM56–5 SB 73–A143, dated June 18,

1999; CFM56–5B SB 73–A062, dated

June 18, 1999; CFM56–5C SB 73–A078,

dated June 21, 1999.

Differences Between Service Bulletins

and This AD

The referenced SBs describe a onetime inspection. This AD requires

repetitive inspections at every filter

change.

Proposed Inspections and Repair or

Replacement

Since an unsafe condition has been

identified that is likely to exist or