This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

59381

Vol. 65, No. 194

Thursday, October 5, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–205–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–200, Ø200C, Ø300, and

Ø400 Series Airplanes

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

Boeing Model 737–200, ¥200C, ¥300,

and ¥400 series airplanes, that

currently requires repetitive visual and

high frequency eddy current (HFEC)

inspections to detect cracking of the

corners of the door frame and the cross

beams of the aft cargo door, and

corrective actions, if necessary. That

amendment also mandates

accomplishment of a modification to the

aft cargo door, which would terminate

the repetitive inspection requirements.

This action would revise the

compliance time of the terminating

action. The actions specified by this

proposal are intended to prevent fatigue

cracking of the corners of the doorframe

and the crossbeams of the aft cargo door,

which could result in rapid

depressurization of the airplane.

DATES: Comments must be received by

November 20, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

205–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 also

be sent via the Internet using the

following address: 9-anmnprmcomment@faa.gov. Comments sent

via the Internet must contain ‘‘Docket

No. 2000–NM–205–AD’’ in the subject

line and need not be submitted in

triplicate.

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:

Nancy Marsh, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–2028; telephone

(425) 227–2557; 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 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,

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 2000–NM–205–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–205–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On March 24, 2000, the FAA issued

AD 2000–06–13, amendment 39–11654

(65 FR 17583, April 4, 2000), applicable

to certain Boeing Model 737–200,

¥200C, ¥300, and ¥400 series

airplanes, to require repetitive visual

inspections and repetitive high

frequency eddy current (HFEC)

inspections to detect cracking of the

corners of the door frame and the cross

beams of the aft cargo door, and

corrective actions, if necessary. That

amendment also mandates

accomplishment of a modification to the

aft cargo door that terminates the

repetitive inspection requirements. The

actions specified by that AD are

intended to prevent fatigue cracking of

the corners of the door frame and the

cross beams of the aft cargo door, which

could result in rapid depressurization of

the airplane.

Actions Since Issuance of Previous Rule

Since the issuance of that AD, the

FAA has reviewed AD 2000–06–13 and

determined that the compliance times

specified for the terminating action in

paragraph (e) of that AD can be relaxed

somewhat. Paragraph (e) of that AD

states the compliance times as, ‘‘prior to

the accumulation of 12,000 total flight

cycles, or within 4 years after the

effective date of this AD, whichever

occurs later.’’ However, the FAA now

has determined that the terminating

action (modification of the aft cargo

door) could be accomplished within

‘‘12,000 flight cycles or 4 years after the

effective date of this AD, whichever

occurs later.’’ The revision to the

compliance time will permit a

reasonable and adequate amount of time

for operators to accomplish the

59382 Federal Register / Vol. 65, No. 194 / Thursday, October 5, 2000 / Proposed Rules

terminating action, and will not

adversely affect safety.

Editorial Explanation

The FAA also has noted that in

paragraphs (a)(2), (a)(3), (a)(4), and Note

2 of AD 2000–06–13, reference is made

to performing certain actions in

accordance with certain paragraphs (i.e.,

paragraph III.C., paragraph III.E., or

paragraph III.F) of part 1 of the

Accomplishment Instructions of Boeing

Alert Service Bulletin 737–52A1079,

Revision 6, dated November 18, 1999.

While those specific paragraph

references are correct for references to

Revision 5 of the Boeing Alert Service

Bulletin, they are not the correct

paragraph references of Revision 6 of

the alert service bulletin. However, the

correct reference section for both

Revision 5 and Revision 6 is still in part

1 of the Accomplishment Instructions.

Therefore, the FAA has deleted the

references to specific paragraphs of part

1 of the Accomplishment Instructions of

the alert service bulletin and retained

reference only to part 1. Specifying that

the actions must be accomplished in

accordance with ‘‘Part 1 of the

Accomplishment Instructions’’ of either

revision will clarify and correct the

appropriate references.

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

revise AD 2000–06–13 to continue to

require repetitive visual and HFEC

inspections to detect cracking of the

corners of the door frame and the cross

beams of the aft cargo door, and

corrective actions, if necessary. This

proposal also would relieve the existing

compliance time for the terminating

action required by AD 2000–06–13 to

modify the aft cargo door.

Cost Impact

There are approximately 1,636 Model

737 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 707 airplanes of U.S.

registry would be affected by this AD.

The detailed visual inspections that

currently are required by AD 2000–06–

13, and retained in this AD, 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

currently required inspections on U.S.

operators is estimated to be $84,840, or

$120 per airplane, per inspection cycle.

The high frequency eddy current

inspections that would be required by

this proposal would take approximately

4 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

inspections on U.S. operators is

estimated to be $169,680, or $240 per

airplane, per inspection cycle.

The modification proposed in this

action would take approximately 144

work hours per airplane to accomplish,

at an average labor rate of $60 per work

hour. Required parts would cost

approximately $4,530 per airplane.

Based on these figures, the estimated

cost impact of the proposed

modification on U.S. operators is

estimated to be $9,311,190, or $13,170

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 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

removing amendment 39–11654 (65 FR

17583, April 4, 2000), and by adding a

new airworthiness directive (AD), to

read as follows:

Boeing: Docket 2000–NM–205–AD. Revises

AD 2000–06–13, Amendment 39–11654.

Applicability: The following airplane

models, certificated in any category.

• Model 737–200 and ¥200C series

airplanes, line numbers 6 through 873

inclusive;

• Model 737–200, ¥200C, ¥300, and

¥400 series airplanes; line numbers 874

through 1642 inclusive; equipped with an aft

cargo door having Boeing part number (P/N)

65–47952–1 or P/N 65–47952–524;

excluding:

1. Those airplanes on which that door has

been modified in accordance with Boeing

Service Bulletin 737–52–1079; or

2. Those airplanes on which the door

assembly having P/N 65–47952–524 includes

four straps (P/N’s 65–47952–139, 65–47952–

140, 65–47952–141, and 65–47952–142) and

a thicker lower cross beam web (P/N 65–

47952–157).

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 (f)(1) 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 corners

of the doorframe and the cross beams of the

aft cargo door, which could result in rapid

depressurization of the airplane, accomplish

the following:

Restatement of the Requirements of AD 98–

25–06

Inspections and Corrective Actions

(a) Within 90 days or 700 flight cycles after

December 24, 1998 (the effective date of AD

Federal Register / Vol. 65, No. 194 / Thursday, October 5, 2000 / Proposed Rules 59383

98–25–06, amendment 39–10931), whichever

occurs later, perform an internal detailed

visual inspection to detect cracking of the

corners of the door frame and the cross

beams of the aft cargo door, in accordance

with Boeing Service Bulletin 737–52–1079,

Revision 5, dated May 16, 1996, or Boeing

Alert Service Bulletin 737–52A1079,

Revision 6, dated November 18, 1999.

(1) If no cracking is detected, accomplish

the requirements of either paragraph (a)(1)(i)

or (a)(1)(ii) of this AD.

(i) Repeat the internal visual inspection

thereafter at intervals not to exceed 4,500

flight cycles. Or

(ii) Prior to further flight, modify the

corners of the doorframe and the crossbeams

of the aft cargo door in accordance with the

service bulletin. Accomplishment of such

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(1)(i) of this AD.

(2) If any cracking is detected in the upper

or lower cross beams, prior to further flight,

modify the cracked beam in accordance with

Part I of the Accomplishment Instructions of

the service bulletin. Accomplishment of such

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(1)(i) of this AD for the repaired

beam.

(3) If any cracking is detected in the

forward or aft upper door frame, prior to

further flight, repair the frame and modify

the corners of the door frame of the aft cargo

door, in accordance with Part I of the

Accomplishment Instructions of the service

bulletin, except as provided by paragraph (b)

of this AD. Accomplishment of such

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(1)(i) of this AD for the upper

doorframe.

Note 2: Cracks of the forward or aft upper

door frame, regardless of length, must be

repaired prior to further flight in accordance

with Part I of the Accomplishment

Instructions of the service bulletin.

(4) If any cracking is detected in the

forward or aft lower door frame, prior to

further flight, replace the damaged frame

with a new frame, and modify the corners of

the door frame of the aft cargo door, in

accordance with Part I of the

Accomplishment Instructions of the service

bulletin. Accomplishment of such

modification constitutes terminating action

for the repetitive inspection requirements of

paragraph (a)(1)(i) of this AD for the lower

doorframe.

(b) Where Boeing Service Bulletin 737–52–

1079, Revision 5, dated May 16, 1996, or

Boeing Alert Service Bulletin, 737–52A1079,

Revision 6, dated November 18, 1999,

specifies that certain repairs are to be

accomplished in accordance with

instructions received from Boeing, this AD

requires that, prior to further flight, such

repairs be accomplished in accordance with

a method approved by the Manager, Seattle

Aircraft Certification Office (ACO), FAA.

New Requirements of This AD

Inspections and Corrective Actions

(c) If any cracking of the outer chord of the

upper or lower cross beams of the aft cargo

door is detected as a result of any inspection

required by paragraph (a) of this AD, prior to

further flight, repair in accordance with a

method approved by the Manager, Seattle

ACO; Boeing Alert Service Bulletin, 737–

52A1079, Revision 6, dated November 18,

1999; or in accordance with data meeting the

type certification basis of the airplane

approved by a Boeing Company Designated

Engineering Representative who has been

authorized by the FAA to make such

findings.

(d) Within 4,500 flight cycles or one year

after the effective date of this AD, whichever

occurs later: Perform a high frequency eddy

current inspection (HFEC) to detect cracking

of the four corners of the door frame of the

aft cargo door, in accordance with the

procedures specified in Boeing 737

Nondestructive Test Manual, Part 6, Chapter

51–00–00 (Figure 4 or Figure 23), or Boeing

Alert Service Bulletin, 737–52A1079,

Revision 6, dated November 18, 1999;

(1) If no cracking of the corners of the

doorframe of the aft cargo door is detected,

repeat the HFEC inspections thereafter at

intervals not to exceed 4,500 flight cycles

until accomplishment of the modification

specified in paragraph (e) of this AD.

(2) If any cracking of the corners of the

door frame of the aft cargo door is detected,

prior to further flight, replace the damaged

frame with a new frame, and modify the four

corners of the door frame, in accordance with

Parts II and III of the Accomplishment

Instructions of Boeing Service Bulletin 737–

52–1079, Revision 5, dated May 16, 1996, or

Boeing Alert Service Bulletin 737–52A1079,

Revision 6, dated November 18, 1999.

Accomplishment of such modification

constitutes terminating action for the

repetitive inspection requirements of

paragraph (d)(1) of this AD for that

doorframe.

Terminating Action

(e) Within 4 years or 12,000 flight cycles

after the effective date of this AD, whichever

occurs later: Modify the four corners of the

door frame and the cross beams of the aft

cargo door, in accordance with Part II of the

Accomplishment Instructions of Boeing

Service Bulletin 737–52–1079, Revision 5,

dated May 16, 1996, or Boeing Alert Service

Bulletin 737–52A1079, Revision 6, dated

November 18, 1999. Accomplishment of that

modification constitutes terminating action

for the repetitive inspection requirements of

this AD.

Note 3: Accomplishment of the

modification required by paragraph (a) of AD

90–06–02, amendment 39–6489, is

considered acceptable for compliance with

paragraph (e) of this AD.

Note 4: Modification of the corners of the

door frame and the cross beams of the aft

cargo door accomplished prior to the

effective date of this AD in accordance with

Boeing Service Bulletin 737–52–1079, dated

December 16, 1983; Revision 1, dated

December 15, 1988; Revision 2, dated July 20,

1989; Revision 3, dated May 17, 1990;

Revision 4, dated February 21, 1991; is

considered acceptable for compliance with

paragraph (e) of this AD.

Alternative Methods of Compliance

(f)(1) 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

ACO. 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.

(2) Alternative methods of compliance,

approved previously in accordance with AD

98–25–06, amendment 39–10931, are

approved as alternative methods of

compliance with this AD.

Note 5: 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

(g) 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

September 29, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–25534 Filed 10–4–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–80–AD]

RIN 2120–AA64

Airworthiness Directives; CL–604

Variant of Bombardier Model Canadair

CL–600–2B16 Series Airplanes

Modified in Accordance With

Supplemental Type Certificate

SA8060NM–D, SA8072NM–D, or

SA8086NM–D

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 Model CL–

604 variant of Bombardier Model

Canadair CL–600–2B16 series airplanes

modified in accordance with certain

Supplemental Type Certificates that

currently requires that the fuel service

panel maintenance light on the fuel

service panel be disconnected. This

action would require modification of the

wiring of the fuel port flood light (which

is the name given to the fuel service