Federal Register / Vol. 66, No. 108 / Tuesday, June 5, 2001 / Proposed Rules 30107

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

adding the following new airworthiness

directive:

Boeing: Docket 2000–NM–378–AD.

Applicability: Model 707 and 720 series

airplanes, listed in Boeing Service Bulletin

1541, Revision 3, dated February 15, 1967;

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 fatigue cracking of the front

spar fitting on the outboard engine nacelle,

which could reduce the structural integrity of

the nacelle, and result in separation of the

engine from the airplane, accomplish the

following:

Preventive Modification

(a) Prior to the accumulation of 20,000 total

flight cycles, or within 24 months after the

effective date of this AD, whichever occurs

later, install the preventive modification of

the front spar fitting on the outboard engine

nacelle. Do the modification (including

replacement of the front spar fitting with a

new, improved (stronger) fitting, and

modification of the front spar chord to

distribute stress loads over the entire front

spar fitting) according to Boeing Service

Bulletin 1541, Revision 3, dated February 15,

1967.

Note 2: Modification of the front spar

fitting on the outboard engine nacelle

(including replacement of the front spar

fitting with a new, improved (stronger)

fitting, and modification of the front spar

chord to distribute stress loads over the

entire front spar fitting) accomplished prior

to the effective date of this AD according to

Boeing Service Bulletin 1541, dated July 1,

1962; Revision 1, dated January 29, 1963;

Revision 2, dated February 11, 1964; or

Supplement 1541(R–2)A, dated April 2,

1964; is acceptable for compliance with the

requirements of paragraph (a) of this AD.

Spares

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

person shall install a front spar fitting, part

number 65–2532 or 65–2532–5, on the

outboard engine nacelle on any airplane.

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, Seattle

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, Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(d) 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 May 30,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–14045 Filed 6–4–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–373–AD]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model DH.125, HS.125, BH.125, and

BAe 125 (U–125 and C–29A) Series

Airplanes, and Hawker 800, Hawker

800 (U–125A), Hawker 800XP, and

Hawker 1000 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 Raytheon Model DH.125,

HS.125, BH.125, and BAe 125 (U–125

and C–29A) series airplanes, and

Hawker 800, Hawker 800 (U–125A),

Hawker 800XP, and Hawker 1000

airplanes. This proposed AD would

require an inspection for cracking or

corrosion of the cylinder head lugs of

the main landing gear (MLG) actuator

and follow-on/corrective actions. This

proposed AD is prompted by reports of

attachment lugs cracking at the actuator

cylinder head. This action is necessary

to prevent separation of the cylinder

head lugs, which could prevent the

MLG from extending and result in a

partial gear-up landing. This action is

intended to address the identified

unsafe condition.

DATES: Comments must be received by

July 20, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

373–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. 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–373–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

Raytheon Aircraft Company,

Department 62, 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, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Wichita, Kansas.

FOR FURTHER INFORMATION CONTACT:

David Ostrodka, Aerospace Engineer,

Airframe Branch, ACE–118W, FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, Wichita,

Kansas 67209; telephone (316) 946–

4129; fax (316) 946–4407.

SUPPLEMENTARY INFORMATION:

30108 Federal Register / Vol. 66, No. 108 / Tuesday, June 5, 2001 / Proposed Rules

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 action 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,

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 action

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 2000–NM–373–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–373–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

cracking of the cylinder head lugs of the

main landing gear (MLG) actuator. Such

cracking of the cylinder heads could

result in separation of the cylinder head

lugs, which could prevent the MLG

from extending. This condition, if not

corrected, could result in a partial gearup landing.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Raytheon Service Bulletin (SB) 32–3391,

dated August 2000. The service bulletin

describes procedures for performing a

one-time eddy current inspection to

detect cracking or corrosion of the

cylinder head lugs of the MLG and

follow-on/corrective actions. The

follow-on/corrective actions include

‘‘vibro-etching’’ the MLG actuator data

plate, painting a blue stripe on the

actuator cylinder head, and replacing

bushings; applying corrosion protection

to the lug bores; and replacing the

actuator with a new or overhauled

actuator or replacement of the actuator

cylinder head with a new cylinder head,

as applicable.

Additional Source of Service

Information

The Raytheon service bulletin

references Precision Hydraulics

Cylinder Maintenance Manual 32–30–

1105 for additional service information

regarding the replacement of the

actuator cylinder head with a new

cylinder head.

Explanation of Requirements of

Proposed Rule

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

require doing the actions specified in

the Raytheon service bulletin described

previously. The actions would be

required to be accomplished in

accordance with the Raytheon service

bulletin described previously.

Cost Impact

There are approximately 1,000

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

this proposed AD would affect 650

airplanes of U.S. registry. The proposed

inspection would take approximately 20

work hours per airplane, at an average

labor rate of $60 per work hour. Based

on these figures, we estimate the cost of

the proposed AD on U.S. operators to be

$780,000, or $1,200 per airplane.

The cost impact figure discussed

above is 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.

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

adding the following new airworthiness

directive:

Raytheon Aircraft Company: Docket 2000–

NM–373–AD.

Applicability: Model DH.125, HS.125,

BH.125, and BAe 125 (U–125 and C–29A)

series airplanes, and Hawker 800, Hawker

800 (U–125A), Hawker 800XP, and Hawker

1000 airplanes, as listed in Raytheon Service

Bulletin SB 32–3391, dated August 2000;

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

Federal Register / Vol. 66, No. 108 / Tuesday, June 5, 2001 / Proposed Rules 30109

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 separation of the cylinder head

lugs, which could prevent the main landing

gear (MLG) from extending and result in a

partial gear-up landing, do the following:

Inspection

(a) Perform an eddy current inspection of

the actuator cylinder head lugs for cracking

or corrosion per Raytheon Service Bulletin

SB 32–3391, dated August 2000, at the time

specified in paragraph (a)(1), (a)(2), (a)(3), or

(a)(4) of this AD, as applicable.

(1) For actuator cylinder heads that have

3,000 or less total landings as of the effective

date of this AD: Perform the eddy current

inspection within 24 months after the

effective date of this AD.

(2) For actuator cylinder heads that have

3,001 to 4,000 total landings as of the

effective date of this AD: Perform the eddy

current inspection within 6 months after the

effective date of this AD.

(3) For actuator cylinder heads that have

been in service for more than 7 years as of

the effective date of this AD: Perform the

eddy current inspection within 6 months of

the effective date of this AD.

(4) For actuator cylinder heads that have

4,001 or more total landings as of the

effective date of this AD: Perform the eddy

current inspection within 10 landings after

the effective date of this AD.

If No Cracking or Corrosion

(b) If no cracking or corrosion is found

during the inspection required by paragraph

(a) of this AD, before further flight,

accomplish the follow-on actions (e.g.,

‘‘vibro-etching’’ the MLG actuator data plate,

painting a blue stripe on the actuator

cylinder head to indicate 1⁄32 inch oversize

bushings, replacing bushings, and applying

corrosion protection to the lug bores), per

Raytheon Service Bulletin SB 32–3391, dated

August 2000.

If Any Cracking or Corrosion

(c) If any cracking or corrosion is found

during the inspection required by paragraph

(a) of this AD, before further flight,

accomplish either of the actions specified in

paragraph (c)(1) or (c)(2) of this AD, per

Raytheon Service Bulletin SB 32–3391, dated

August 2000.

(1) Replace the actuator of the MLG with

a new or serviceable actuator, or

(2) Replace the actuator cylinder head with

a new cylinder head.

Note 2: Raytheon Service Bulletin SB 32–

3391, dated August 2000, references

Precision Hydraulics Cylinder Maintenance

Manual (CMM) 32–30–1105 as an additional

source of service information.

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, Wichita

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, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permit

(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.

Issued in Renton, Washington, on May 30,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–14044 Filed 6–4–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–220–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 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 all Boeing

Model 747 series airplanes, that

currently requires a one-time inspection

of the fuselage skin adjacent to the drag

splice fitting to detect cracking, and

follow-on actions, if necessary. This

action would mandate new repetitive

inspections for cracking of the fuselage

skin adjacent to the drag splice fitting.

This proposal is prompted by reports of

fatigue cracking in the fuselage skin and

adjacent structure. The actions specified

by the proposed AD are intended to

detect and correct such cracking, which

could result in reduced structural

integrity of the fuselage, and consequent

rapid depressurization of the airplane.

DATES: Comments must be received by

July 20, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

220–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 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-anmnprmcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2000–NM–220–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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Rick

Kawaguchi, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1153; fax (425) 227–1181.

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 action 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.