10384 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules

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 39–11327 (64 FR

51190, September 22, 1999), and by

adding a new airworthiness directive

(AD), to read as follows:

Airbus Industrie: Docket 2000–NM–160–AD.

Supersedes AD 99–19–40, Amendment

39–11327.

Applicability: The following airplanes,

certificated in any category and equipped

with a standby generator (FIN 25XE);

excluding airplanes on which Airbus

Modification 12135 has been accomplished:

Model A310 series airplanes on which

Airbus Modification 05910 has been

installed, and Model A300 B4–600, A300 B4–

600R, and A300 F4–600R (Collectively Called

A300–600) series airplanes on which Airbus

Modification 06213 has been installed.

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 (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 excessive vibrations generated

by the mounting configuration of the 15XE

connector, which could cause breakage of the

terminal and mounting lugs on the 15XE

connector in the 101VU panel in the avionics

compartment, resulting in loss of electrical

power from the standby generator,

accomplish the following:

Restatement of Certain Actions Required by

AD 99–19–40

Inspection and Corrective Actions

(a) Prior to the accumulation of 5,000 total

flight hours, or within 600 flight hours after

the effective date of this AD, whichever

occurs later: Accomplish the actions required

by paragraphs (a)(1) and (a)(2) of this AD in

accordance with Airbus All Operators Telex

(AOT) 24–09, Revision 01, dated August 13,

1998.

(1) Perform a detailed visual inspection of

the terminal lugs on the 12XC and 15XE

connectors to detect damage (i.e., overheat,

cracking, twisting, or total rupture). If any

damage is detected, prior to further flight,

replace the terminal lugs with new terminal

lugs, part number (P/N) NSA936501TA1004.

(2) Perform a detailed visual inspection of

the mounting lugs on the 15XE connector to

detect damage (i.e., cracking or breaking). If

any damage is detected, prior to further

flight, accomplish the requirements of either

paragraph (a)(2)(i) or (a)(2)(ii) of this AD.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

(i) Replace connector 15XE with a new

connector, P/N 25811BOSHUNTKL, vendor

code F0214 ECE. Or,

(ii) Repair connector 15XE in accordance

with Airbus AOT 24–09, Section 4.2.2.3.

Repeat the detailed visual inspection

required by paragraph (a)(2) of this AD of the

repaired connector thereafter at intervals not

to exceed 1 week, and repeat the repair with

new cable ties thereafter at intervals not to

exceed 3 months, until the replacement

required by paragraph (a)(2)(i) of this AD is

accomplished.

New Actions Required by This AD

Installation

(b) Within 20 months after the effective

date of this AD, install a new mounting

bracket for the 15XE connector, modify the

cable attachment adjacent to the connector,

and replace certain terminal lugs with lugs

having a thicker contact area, in accordance

with Airbus Service Bulletin A310–24–2080

(for Model A310 series airplanes) or A300–

24–6070 (for Model A300–600 series

airplanes), both dated December 15, 1999, as

applicable.

Replacement

(c) Continue the detailed visual inspection

of a repaired 15XE connector which is

required by paragraph (a)(2)(ii) of this AD at

intervals not to exceed 1 week, and continue

the repair with new cable ties at intervals not

to exceed 3 months, until the repaired 15XE

connector is replaced by a new 15XE

connector.

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,

International Branch, ANM–116, FAA,

Transport 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, 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

(e) 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.

Note 4: The subject of this AD is addressed

in French airworthiness directive 2000–145–

306(B), dated April 5, 2000.

Issued in Renton, Washington, on February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3855 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–159–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 727, 737, 757–200, 757–200CB,

and 757–300 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 727, 737, 757–

200, 757–200CB, and 757–300 series

airplanes. This proposal would require

modification of the latch assembly of

the escape slides. For certain airplanes,

this proposal would also require

installation of a cover assembly on the

trigger housing of the inflation cylinder

on the escape slides. This action is

necessary to prevent failure of an escape

slide to deploy or inflate correctly,

which could result in the slide being

unusable during an emergency

evacuation and consequent injury to

passengers or airplane crewmembers.

This action is intended to address the

identified unsafe condition.

DATES: Comments must be received by

April 2, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules 10385

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000–NM–

159–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 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–159-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:

Keith Ladderud, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2780; 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.

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–159–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–159–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports

indicating that latch assemblies on the

emergency escape slides have failed on

several Boeing Model 727, 737, 757–

200, 757–200CB, and 757–300 series

airplanes. Several operators have

reported failures due to corrosion of the

spring pins in the latch assemblies,

while others have reported finding

discrepant (e.g., deformed or incorrectly

soldered) split rings attaching the chain

assembly to the latch block assembly.

Failed spring pins or discrepant split

rings in the escape slide latch assembly

could result in failure of the escape

slide latch assembly in service, and

consequent failure of the escape slide to

deploy.

The FAA has also received reports

that, during functional tests of escape

slides prior to delivery of Boeing Model

737–600, –700, and –800 series

airplanes, the trigger housing of the

inflation cylinder of an escape slide

caught on the jumper cable of the escape

slide compartment. The interference

between these two parts caused the

escape slide to fail to completely drop

from the door before inflating, which

resulted in the escape slides failing to

inflate correctly.

Failure of an escape slide to deploy or

inflate correctly in an emergency

situation could result in the slide being

unusable during an emergency

evacuation and consequent injury to

passengers or airplane crewmembers.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

the following Boeing Service Bulletins:

Service bulletin Date For model * * * Actions

727–25–0294 May 25, 2000 ................................... 727–100 and 727–200 series ..................... Modification of escape slide latch assembly.

737–25–1405 ......do ............................................... 737–100, –200, –300, –400, and –500 series.Do.

737–25–1403 May 4, 2000 ..................................... 737–600, –700, and –800 series ................ Installation of a cover assembly on the trigger housing of the inflation cylinder on

the escape slides.

737–25–1404 May 25, 2000 ................................... 737–600, –700, and –800 series ................ Modification of escape slide latch assembly.

757–25–0217 ......do ............................................... 757–200 and –200CB series ...................... Do.

757–25–0218 ......do ............................................... 757–300 series ............................................ Do.

The modification of the escape slide

latch assembly for all airplanes involves

replacement of existing spring pins with

new spring pins made from more

corrosion-resistant material. For certain

airplanes, the modification also involves

replacement of the existing split ring,

which attaches the chain assembly to

the latch block assembly, with a clevis.

Boeing Service Bulletin 737–25–1403

refers to BF Goodrich Service Bulletin

5A3307–25–309, dated October 29,

1999, as an additional source of service

information for the installation of a

cover assembly on the trigger housing of

the inflation cylinder on the escape

slides on Model 737–600, –700, and

–800 series airplanes.

10386 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules

Accomplishment of the actions

specified in the applicable service

bulletins 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 applicable service

bulletins described previously, except

as discussed below.

Differences Between Proposed Rule and

Service Bulletins

Operators should note that, although

the service bulletins do not recommend

a specific compliance time, the FAA has

determined that a specific compliance

time is needed to ensure that the

identified unsafe condition is addressed

in a timely manner. In developing an

appropriate compliance time for this

proposed AD for these airplanes, the

FAA considered not only the

manufacturer’s recommendation, but

the degree of urgency associated with

addressing the subject unsafe condition,

and the average utilization of the

affected fleets.

Considering these factors, the FAA

finds a 36-month compliance time for

completing the proposed actions on

Model 727, 737–100, 737–200, 737–300,

737–400, 737–500, 757–200, 757–

200CB, and 757–300 series airplanes to

be warranted, in that this represents an

appropriate interval of time allowable

for affected airplanes to continue to

operate without compromising safety.

For Model 737–600, –700, and –800

series airplanes, the FAA finds an 18-

month compliance time for completing

the proposed actions to be warranted. In

developing an appropriate compliance

time for this proposed AD for these

airplanes, the FAA considered not only

the manufacturer’s recommendations for

installing a cover assembly on the

trigger housing of the inflation cylinder

on the escape slides, but also the degree

of urgency associated with failure of an

escape slide to inflate correctly due to

interference between the trigger housing

of the inflation cylinder and the jumper

cable of the escape slide compartment.

Considering these factors, and the fact

that it will be convenient for affected

operators to modify the escape slide

latch assembly at the same time they

install the cover assembly, the FAA has

determined that 18 months represents

an appropriate interval for affected

airplanes to continue to operate without

compromising safety.

Cost Impact

There are approximately 5,759

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

2,906 airplanes of U.S. registry would be

affected by this proposed AD. The

following table shows the estimated cost

impact for airplanes affected by this AD.

‘‘Action 1’’ is the modification of the

escape slide latch assembly, and

‘‘Action 2’’ is the installation of a cover

assembly on the trigger housing of the

inflation cylinder on the escape slide.

The average labor rate is $60 per work

hour. The cost impact is as follows:

Models/series Action

U.S.-

registered

airplanes

Work hours

per airplane

(estimated)

Parts cost

(estimated

maximum)

Cost per

airplane

(estimated)

Maximum

fleet cost

(estimated)

727 ................................................................................... 1 955 2 $1,068 $1,188 $1,134,540

737–100, –200, –300, –400, –500 .................................. 1 1,156 2 1,192 1,312 1,516,672

737–600, –700, –800 ....................................................... 1 277 2 1,424 1,544 427,688

737–600, –700, –800 ....................................................... 2 277 4 Free 240 66,480

757–200, –200CB, –300 .................................................. 1 518 3 1,602 1,782 923,076

The cost impact figures discussed

above are 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:

Boeing: Docket 2000–NM–159–AD.

Applicability: The following airplanes,

certificated in any category:

Model As listed in * * * Service bulletin date

727–100 and 727–200 series .............................................. Boeing Service Bulletin 727–25–0294 ............................... May 25, 2000.

737–100, –200, –300, –400, and –500 series ..................... Boeing Service Bulletin 737–25–1405 ............................... Do.

Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules 10387

Model As listed in * * * Service bulletin date

737–600, –700, and –800 series ......................................... Boeing Special Attention Service Bulletin 737–25–1403 ... Do.

737–600, –700, and –800 series ......................................... Boeing Service Bulletin 737–25–1404 ............................... Do.

757–200 and –200CB series ............................................... Boeing Service Bulletin 757–25–0217 ............................... Do.

757–300 series ..................................................................... Boeing Service Bulletin 757–25–0218 ............................... Do.

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 failure of an escape slide to

deploy or inflate correctly, which could

result in the slide being unusable during an

emergency evacuation and consequent injury

to passengers or airplane crewmembers,

accomplish the following:

Modification

(a) At the schedule specified in the

following table, do the actions in the ‘‘Do

these actions * * * ’’ column, per the service

bulletin specified in the ‘‘As listed in * * *’’

column:

TABLE 1.—REQUIRED ACTIONS

For model * * * As listed in * * * Dated * * * Do these actions * * * No later than * * *

727–100 and 727–200 series.Boeing Service Bulletin

727–25–0294.

May 25, 2000 .................... Modify the escape slide

latch assembly.

36 months after the effective date of this AD.

737–100, –200, –300,

–400, and –500 series.

Boeing Service Bulletin

737–25–1405.

......do ................................ ......do ................................ Do.

737–600, –700, and –800

series.

Boeing Special Attention

Service Bulletin 737–25–

1403.

May 4, 2000 ...................... Install a cover assembly

on the trigger housing of

the inflation cylinder on

the escape slides.

18 months after the effective date of this AD.

737–600, –700, and –800

series.

Boeing Service Bulletin

737–25–1404.

May 25, 2000 .................... Modify the escape slide

latch assembly.

Do.

757–200 and –200CB series.Boeing Service Bulletin

757–25–0217.

......do ................................ ......do ................................ 36 months after the effective date of this AD.

757–300 series .................. Boeing Service Bulletin

757–25–0218.

......do ................................ ......do ................................ Do.

Spares

(b) After the effective date of this AD, no person may install an escape slide assembly or escape slide latch assembly listed

in the ‘‘Existing Part Number’’ column of the table under paragraph 2.E. in the following service bulletins, on any airplane:

TABLE 2.—SPARE PARTS

For Models * * * Listed in * * * Service bulletin date

727–100 and 727–200 series ......................... Boeing Service Bulletin 727–25–0294 .............................................. May 25, 2000

737–100, –200, –300, –400, and –500 series Boeing Service Bulletin 737–25–1405 .............................................. Do.

737–600, –700, and –800 series .................... Boeing Special Attention Service Bulletin 737–25–1403 ................. May 4, 2000.

737–600, –700, and –800 series .................... Boeing Service Bulletin 737–25–1404 .............................................. May 25, 2000.

757–200 and –200CB series .......................... Boeing Service Bulletin 757–25–0217 .............................................. Do.

757–300 series ............................................... Boeing Service Bulletin 757–25–0218 .............................................. Do.

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 2: 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 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 February

9, 2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–3856 Filed 2–14–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–330–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Powered

By Pratt & Whitney JT9D–3 and –7

Series Engines

AGENCY: Federal Aviation

Administration, DOT.