7182 Federal Register / Vol. 62, No. 32 / Tuesday, February 18, 1997 / Proposed Rules

of the tail tank, in accordance with the alert

service bulletin.

(i) Condition 1. If no damage to the fuel

pipe assembly is detected, accomplish the

requirements of either paragraph (a)(2)(i)(A)

or (a)(2)(i)(B) of this AD at the times specified

in that paragraph.

(A) Condition 1, Option 1. Thereafter,

repeat the visual inspections required by

paragraph (a) of this AD at intervals not to

exceed 600 flight hours; or

(B) Condition 1, Option 2. Install a

temporary doubler on the fuel pipe assembly

in accordance with the alert service bulletin

and, thereafter, repeat the visual inspections

required by paragraph (a) of this AD at

intervals not to exceed 15 months.

(ii) Condition 2. If damage is found that is

within the limits specified by the alert

service bulletin, prior to further flight, install

a temporary doubler on the fuel pipe

assembly. Thereafter, repeat the visual

inspections required by paragraph (a) of this

AD at intervals not to exceed 15 months.

(iii) Condition 3. If damage is found that is

outside the limits specified by the alert

service bulletin, prior to further flight,

replace the fuel pipe assembly with a new or

serviceable assembly; and accomplish the

requirements of either paragraph (a)(2)(iii)(A)

or (a)(2)(iii)(B) of this AD at the time

specified in that paragraph.

(A) Condition 3, Option 1. Thereafter,

repeat the visual inspections required by

paragraph (a) of this AD at intervals not to

exceed 600 flight hours; or

(B) Condition 3, Option 2. Install a

temporary doubler on the fuel pipe assembly;

and repeat the visual inspections required by

paragraph (a) of this AD, thereafter, at

intervals not to exceed 15 months.

(Replacement of the fuel pipe assembly with

a serviceable pipe assembly that has been

repaired by welding a doubler in the area of

potential damage, does not require the

installation of a temporary doubler.)

New Requirements of this AD

(b) Within 24 months after the effective

date of this AD, accomplish the requirements

of paragraphs (b)(1) and (b)(2) of this AD, as

applicable.

(1) For airplanes on which the temporary

protective doubler has been installed on the

fuel pipe assembly in accordance with

McDonnell Douglas Alert Service Bulletin

MD11–28A083, dated March 13, 1996:

Remove the clamps and the temporary

protective doubler installed on the fuel

transfer pipe, in accordance with McDonnell

Douglas Service Bulletin MD11–28–089,

dated October 24, 1996. Prior to further flight

following accomplishment of the removal,

accomplish the requirements of paragraph

(a)(2) of this AD.

(2) For all airplanes: Install the fuel transfer

pipe of the tail tank and support brackets and

clamps of the fuel feed pipe of engine No. 2,

in accordance with McDonnell Douglas

Service Bulletin MD11–28–089, dated

October 24, 1996. Accomplishment of this

installation constitutes terminating action for

the requirements of this AD.

(c)(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, Los

Angeles Aircraft Certification Office (ACO),

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, Los Angeles ACO.

(2) Alternative methods of compliance that

concern the use of an alternate material in

lieu of the specified temporary doubler,

which were approved previously in

accordance with AD 96–10–07, amendment

39–9612, are not considered to be approved

as alternative methods of compliance with

this AD.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(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

10, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3842 Filed 2–14–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–283–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–11 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 McDonnell Douglas Model MD–

11 series airplanes. This proposal would

require a one-time inspection to detect

riding, chafing, or damage of the wire

bundles adjacent to the disconnect

panel bracket of the observer’s station.

The proposed AD also would require

repair or replacement of damaged wires

with new or serviceable wires;

installation of anti-chafing sleeving on

the wire bundles, if necessary; and

installation of grommet along the entire

upper aft edge of the disconnect panel

bracket. This proposal is prompted by a

report indicating that the circuit

breakers tripped on a Model MD–11

series airplane due to inflight arcing

behind the avionics circuit breaker

panel as a result of chafing of the wire

bundles adjacent to the disconnect

panel bracket assembly. The actions

specified by the proposed AD are

intended to detect and correct such

chafing, which could result in a fire in

the wire bundles and smoke in the

cockpit.

DATES: Comments must be received by

March 28, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

283–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.

The service information referenced in

the proposed rule may be obtained from

McDonnell Douglas Corporation, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Department C1–L51 (2–60). This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Brett Portwood, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130L, FAA, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California 90712;

telephone (310) 627–5347; fax (310)

627–5210.

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.

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.
Federal Register / Vol. 62, No. 32 / Tuesday, February 18, 1997 / Proposed Rules 7183

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 96–NM–283–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–103, Attention: Rules Docket No.

96–NM–283–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA received a report indicating

that the circuit breakers tripped on a

Model MD–11 series airplane during

flight due to arcing behind the avionics

circuit breaker panel. Investigation

revealed that the arcing was caused by

chafing of the wire bundles adjacent to

the disconnect panel bracket assembly.

Such chafing, if not detected and

corrected, could result in a fire in the

wire bundles and smoke in the cockpit.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

McDonnell Douglas Service Bulletin

MD11–24–111, dated December 3, 1996.

The service bulletin describes

procedures for a one-time inspection to

detect riding, chafing, or damage of the

wire bundles adjacent to the disconnect

panel bracket of the observer’s station.

The service bulletin also describes

procedures for repair or replacement of

damaged wires with new or serviceable

wires; installation of anti-chafing

sleeving on the wire bundles, if

necessary; and installation of grommet

along the entire upper aft edge of the

disconnect panel bracket.

Accomplishment of the installations

will minimize potential arcing, wiring

damage, and resultant loss of aircraft

systems.

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 a one-time inspection to detect

riding, chafing, or damage of the wire

bundles adjacent to the disconnect

panel bracket of the observer’s station.

The proposed AD also would require

repair or replacement of damaged wires

with new or serviceable wires;

installation of anti-chafing sleeving on

the wire bundles, if necessary; and

installation of grommet along the entire

upper aft edge of the disconnect panel

bracket. The actions would be required

to be accomplished in accordance with

the service bulletin described

previously.

Cost Impact

There are approximately 86

McDonnell Douglas Model MD–11

series airplanes of the affected design in

the worldwide fleet. The FAA estimates

that 45 airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 3 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. The cost for

required parts would be negligible.

Based on these figures, the cost impact

of the proposed AD on U.S. operators is

estimated to be $8,100, or $180 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.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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:

MCDONNELL DOUGLAS: Docket 96–NM–283–

AD.

Applicability: Model MD–11 series

airplanes, as listed in McDonnell Douglas

Service Bulletin MD11–24–111, dated

December 3, 1996; 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 (b) 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 detect and correct chafing of the wire

bundles adjacent to the disconnect panel

bracket assembly and consequent inflight

arcing behind the avionics circuit breaker,

which could result in a fire in the wire

bundles and smoke in the cockpit,

accomplish the following:

(a) Within 6 months after the effective date

of this AD: Perform a one-time inspection to

detect riding, chafing, or damage of the wire

bundles adjacent to the disconnect panel

bracket of the observer’s station, in

accordance with McDonnell Douglas Service

Bulletin MD11–24–111, dated December 3,

1996.

(1) Condition 1. If any riding or chafing is

found, and if any damage is found: Prior to

further flight, repair or replace any damaged

wires with new or serviceable wires; install

anti-chafing sleeving on the wire bundles;

and install a grommet along the entire upper

aft edge of the disconnect panel bracket; in

accordance with the service bulletin.

(2) Condition 2. If any riding or chafing is

found, but no damage is found: Prior to

further flight, install anti-chafing sleeving on

the wire bundles, and install a grommet

along the entire upper aft edge of the
7184 Federal Register / Vol. 62, No. 32 / Tuesday, February 18, 1997 / Proposed Rules

disconnect panel bracket, in accordance with

the service bulletin.

(3) Condition 3. If no riding, chafing, or

damage is found: Prior to further flight,

install a protective grommet along the entire

upper aft edge of the disconnect panel

bracket in accordance with the service

bulletin.

(b) 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, Los

Angeles Aircraft Certification Office (ACO),

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, Los Angeles ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

(c) 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

10, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3841 Filed 2–14–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–64–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

Equipped with Pratt & Whitney

Turbofan Engines

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 Airbus Model A310 and A300–

600 series airplanes. This proposal

would require flow checks of the

hydraulic pump drain system to ensure

that the system is not clogged, and

correction of any discrepancy.

Additionally, the proposed AD would

require replacement of the existing seal

of the accessory gearbox with a new,

improved seal assembly; this

replacement would terminate the

requirement for repetitive flow checks.

This proposal is prompted by reports

indicating that hydraulic fluid had

contaminated the engine oil system as a

result of failure of the seal of the

hydraulic pump shaft. The actions

specified by the proposed AD are

intended to prevent clogging of the

hydraulic pump drain system, which

could cause failure of the seal of the

hydraulic pump shaft and subsequent

contamination of the engine accessory

gearbox oil; this condition could result

in an in-flight engine shutdown.

DATES: Comments must be received by

March 28, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

64–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.

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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 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 notice may be changed in light

of the comments received.

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 96–NM–64–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–103, Attention: Rules Docket No.

96–NM–64–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on certain Airbus

Model A310 and A300–600 series

airplanes. The DGAC advises that it has

received reports of engine oil

contamination on both of these models

of airplanes. Investigation revealed that

the contamination was due to failure of

the seal of the green hydraulic pump

shaft as a result of clogging of the

hydraulic pump drain system. The seal

is insufficient to handle the increase in

the backflow pressure when the

hydraulic pump drain system is

clogged. Failure of the seal of the green

hydraulic pump shaft, if not corrected,

could permit contamination of the

engine accessory gearbox oil, and result

in an in-flight engine shutdown.

Explanation of Relevant Service

Information

Airbus has issued the following

service bulletins which describe

procedures for performing repetitive

flow checks of the hydraulic pump

drain system to ensure that the system

is not clogged, and correction of any

discrepancy.

1. For Model A310 series airplanes:

Airbus Service Bulletin A310–72–2022,

dated February 16, 1993 (for airplanes

on which Pratt & Whitney JT9D–7R4D1

and 7R4E1 engines are installed); and

Airbus Service Bulletin A310–72–2023,

Revision 1, dated December 22, 1993

(for airplanes on which Pratt & Whitney

PW4152 and PW 4156A engines are

installed).

2. For Model A300–600 series

airplanes: Airbus Service Bulletin

A300–72–6018, Revision 1, dated

December 22, 1993 (for airplanes on

which Pratt & Whitney JT9D–7R4H1

engines are installed); and Airbus

Service Bulletin A300–72–6019,

Revision 1, dated December 22, 1993

(for airplanes on which Pratt & Whitney

PW4158 engines are installed).