Federal Register / Vol. 66, No. 108 / Tuesday, June 5, 2001 / Proposed Rules 30105

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:

BAe Systems (Operations) Limited (Formerly

British Aerospace Regional Aircraft):

Docket 2001–NM–06–AD.

Applicability: Model BAe 146 and Avro

146–RJ series airplanes, certificated in any

category, as listed in BAe Systems

(Operations) Limited Inspection Service

Bulletin ISB.21–148, Revision 1, dated

February 6, 2001.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 the installation of incorrect

pressurization discharge valves and cabin

pressure controllers, which could subject the

airframe to excess stress and adversely affect

the airframe fatigue life, accomplish the

following:

Parts Identification

(a) As specified in paragraph (a)(1) or

(a)(2), as applicable, of this AD: Identify the

part numbers of the pressurization discharge

valves and cabin pressure controllers to

determine if any installed part is incorrect, as

defined by and in accordance with BAe

Systems (Operations) Limited Inspection

Service Bulletin ISB.21–148, Revision 1,

dated February 6, 2001.

(1) For airplanes post-Modification

HCM50258A: Identify the part numbers

within 30 days after the effective date of this

AD; and, if any part is incorrect, limit the

airplane ceiling to 31,000 feet until the

incorrect part is replaced, as specified by

paragraph (b) of this AD.

(2) For airplanes pre-Modification

HCM50258A: Identify the part numbers

within 6 months after the effective date of

this AD.

Corrective Action

(b) For any incorrect part identified in

accordance with paragraph (a) of this AD:

Within 500 flight cycles thereafter, replace it

with a new, correct part, in accordance with

BAe Systems (Operations) Limited Inspection

Service Bulletin ISB.21–148, Revision 1,

dated February 6, 2001. Prior to further flight

thereafter, perform a structural inspection

and accomplish applicable corrective actions,

in accordance with a method approved by

the Manager, International Branch, ANM–

116, Transport Airplane Directorate, FAA; or

the The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC) (or its delegated agent).

Note 2: Accomplishment of the actions

specified in this AD in accordance with BAe

Systems (Operations) Limited Inspection

Service Bulletin ISB.21–148, dated November

17, 2000, is also acceptable for compliance

with the requirements of this AD.

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,

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 3: 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

(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.

Note 4: The subject of this AD is addressed

in British airworthiness directive 003–11–

2000.

Issued in Renton, Washington, on May 30,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–14046 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–378–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 707 and 720 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 Boeing Model 707 and 720 series

airplanes. This proposal would require

a preventive modification of the front

spar fitting on the outboard engine

nacelle. This action is necessary 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. 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–

378–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–378–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:

Duong Tran, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2773; 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

30106 Federal Register / Vol. 66, No. 108 / Tuesday, June 5, 2001 / Proposed Rules

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–378-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–378–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports that

fatigue cracks have been found in the

front spar fitting on the outboard engine

nacelle on certain Boeing Model 707

and 720 series airplanes. The cracks

originated at the rearmost of the seven

fasteners which attach the front spar

fitting to the front spar chord. Such

cracking, if not corrected, could reduce

the structural integrity of the nacelle,

and result in separation of the engine

from the airplane.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Service Bulletin 1541, Revision

3, dated February 15, 1967, which

describes procedures for, among other

actions, installation of a preventive

modification of the front spar fitting on

the outboard engine nacelle. The

modification involves 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. Accomplishment of

the actions specified in the service

bulletin 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 products of this same

type design, the proposed AD would

require accomplishment of the actions

specified in the service bulletin

described previously, except as

discussed below.

Differences Between Proposed Rule and

Service Bulletin

This proposed rule differs from the

service bulletin in the compliance time

for the proposed modification. For

certain airplanes, the service bulletin

recommends accomplishment of the

modification of the front spar fitting, but

does not specify a compliance time; for

other airplanes, the service bulletin

specifies that the modification is

optional and may be installed on an

attrition basis. This proposed AD would

require installation of the modification

prior to the accumulation of 20,000 total

flight cycles, or within 24 months after

the effective date of this AD, whichever

occurs later. In developing an

appropriate compliance time for this

AD, the FAA considered not only the

manufacturer’s recommendation, but

the degree of urgency associated with

addressing the subject unsafe condition,

the average utilization of the affected

fleet, and the time necessary to perform

the actions. In light of all of these

factors, the FAA finds that the proposed

compliance time for completing the

required actions represents an

appropriate interval of time allowable

for affected airplanes to continue to

operate without compromising safety.

The proposed rule also differs from

the service bulletin in that it would not

require the repetitive inspections to

detect cracking of the front spar fitting,

which are described in the service

bulletin. The decision to mandate the

preventive modification of the front spar

fitting is based on the FAA’s

determination that long-term continued

operational safety will be better assured

by design changes to remove the source

of the problem, rather than by repetitive

inspections. Long-term inspections may

not provide the degree of safety

assurance necessary for the transport

airplane fleet. This, coupled with a

better understanding of the human

factors associated with numerous

continual inspections, has led the FAA

to consider placing less emphasis on

inspections and more emphasis on

design improvements. The proposed

modification requirement is consistent

with these findings.

Operators should note that Section 3.,

Part II, ‘‘l,’’ of the service bulletin refers

to an incorrect part number for the new,

improved front spar fitting. That item

reads, ‘‘Install applicable new fitting

65–13347–4* * *’’; the FAA has

determined that the correct part number

for the new, improved fitting in this

case is 65–13347–5. Figure 1 of the

service bulletin references the correct

part number.

Cost Impact

There are approximately 13 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 3

airplanes of U.S. registry would be

affected by this proposed AD, that it

would take approximately 64 work

hours per airplane to accomplish the

proposed modification, and that the

average labor rate is $60 per work hour.

Required parts would cost

approximately $1,300 per airplane.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be $15,420, or $5,140 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

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: