10382 Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–160–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310, and Model A300 B4–600, A300

B4–600R, and A300 F4–600R

(Collectively Called A300–600) 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

Airbus Model A310 and A300–600

series airplanes. The existing AD

requires a detailed visual inspection to

detect damage to the terminal lugs on

the 12XC and 15XE connectors and the

mounting lugs on the 15XE connector;

corrective actions, if necessary; and

certain conditional repetitive

inspections. This action would add

requirements for installation of a new

mounting bracket for the 15XE

connector, modification of the cable

attachment adjacent to the connector,

and replacement of certain terminal lugs

on the 15XE connector by terminal lugs

with a thicker contact area. This

proposal is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by the proposed AD are

intended 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

connectors in the 101VU panel in the

avionics compartment, resulting in loss

of electrical power from the standby

generator.

DATES: Comments must be received by

March 19, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2000-NM–

160-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–160-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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Dan

Rodina, Aerospace Engineer, ANM–116,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2125; fax (425) 227–1149.

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 action. 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–160–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–160–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On September 10, 1999, the FAA

issued AD 99–19–40, amendment 39–

11327 (64 FR 51190, September 22,

1999), applicable to certain Model A310

and Model A300–600 series airplanes.

That AD requires a detailed visual

inspection to detect damage to the

terminal lugs on the 12XC and 15XE

connectors and the mounting lugs on

the 15XE connector; and repair or

replacement of the terminal lugs or the

15XE connector with new parts, if

necessary. That action was prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

requirements of that AD are intended to

detect and correct broken terminal and

mounting lugs on the 12XC and the

15XE connectors in the 101VU panel in

the avionics compartment, which could

result in loss of electrical power from

the standby generator.

Actions Since Issuance of AD 99–19–40

In the Notice of Proposed Rule

Making that preceded issuance of AD

99–19–40, the FAA stated that

preliminary indications were that the

mounting configuration of connector

12XE was transmitting vibration to the

terminal lugs of both connectors and to

the mounting lugs of connector 15XE.

Subsequently, in the preamble to AD

99–19–40, the FAA stated that the

actions required by that AD were

considered ‘‘interim action’’ until final

action was identified, at which time the

agency might consider further

rulemaking.

Since the issuance of that AD,

laboratory analyses and flight tests

conducted by Airbus have shown that

excessive vibration is generated by the

mounting configuration of the 15XE

connector. That condition, if not

corrected, could result in breakage of

the mounting lugs on the 15XE

connector and the terminal lugs on the

15XE and 12XC connectors in the

101VU panel in the avionics

compartment, resulting in loss of

electrical power from the standby

generator to the AC essential bus.

Therefore, the FAA has determined that

Federal Register / Vol. 66, No. 32 / Thursday, February 15, 2001 / Proposed Rules 10383

further rulemaking action is indeed

necessary, and this proposed AD

follows from that determination.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletins

A310–24–2080 (for Model A310 series

airplanes) and A300–24–6070 (for

Model A300–600 series airplanes), both

dated December 15, 1999. The service

bulletins describe procedures for

replacing the mounting bracket for the

15XE connector, modifying the cable

attachment adjacent to the connector,

and replacing certain terminal lugs on

the 15XE connector with lugs having a

thicker contact area. The modification is

intended to eliminate excessive

vibration and prevent the possible

consequent breakage of the mounting

lugs on the 15XE connector and the

terminal lugs on the 15XE and 12XC

connectors. The Direction Generale de

l’Aviation Civile (DGAC), which is the

airworthiness authority for France,

classified these service bulletins as

mandatory and issued French

airworthiness directive 2000–145–

306(B), dated April 5, 2000, in order to

ensure the continued airworthiness of

these airplanes in France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

An unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States. The proposed AD would

supersede AD 99–19–40 to continue to

require inspecting the terminal lugs on

the 12XC and 15XE connectors and the

mounting lugs on the 15XE connectors

for damage, and corrective action, if

necessary. The proposed AD would add

requirements for installation of a new

mounting bracket for the 15XE

connector, modification of the cable

attachment adjacent to the connector,

and replacement of certain terminal lugs

on the 15XE connector with lugs having

a thicker contact area. The proposed AD

would require accomplishment of the

actions specified in the service bulletins

described previously, as applicable.

Explanation of Applicability of the

Proposed AD

Sections of AD 99–19–40 that pertain

to applicability identify certain Airbus

modifications by incorrect numbers.

Those modification numbers have been

corrected in this proposed AD.

Because of this error in modification

numbers in AD 99–19–40, it is possible

that certain airplanes—Model A310

series airplanes on which Airbus

Modification 05910 had been installed

and Model A300–600 series airplanes

on which Airbus Modification 06213

had been installed—did not comply

with that AD. Therefore, the

requirements of AD 99–19–40 are restated in the proposed AD. The

compliance time for the inspection

would be reset from the effective date of

the AD.

Operators of these airplanes who did

comply with the requirements of AD

99–19–40 need not repeat the detailed

visual inspections and corrective action

required by that AD. However, such

operators who elected to repair rather

than replace a 15XE connector with

damaged mounting lugs must continue

to perform periodic inspections and

periodic re-repairs of the connector

until it is replaced with a new 15XE

connector.

Additional Changes to Applicability

This proposed AD and AD 99–19–40

are applicable to the same airplane

models. However, the model

designation of the affected airplanes has

been revised to conform to the type

certificate data sheet listing for these

airplanes. This proposed AD identifies

these airplanes as ‘‘Model A310, and

Model A300 B4–600, A300 B4–600R,

and A300 F4–600R series airplanes.’’

Cost Impact

There are approximately 109

airplanes of U.S. registry that would be

affected by this proposed AD. The

following information describes the

estimated cost impact on U.S. operators

of the proposed actions:

Action Work hours Hourly labor

rate Parts cost Per-airplanecost Fleet cost

Inspection ................................................................................................. 2 $60 $0 $120 $13,080

Modification .............................................................................................. 5 60 490 790 86,110

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 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.

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