Federal Register / Vol. 60, No. 41 / Thursday, March 2, 1995 / Rules and Regulations 11619

Administrator, the Federal Aviation

Administration amends 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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–04–07 McDonnell Douglas: Amendment

39–9159. Docket 94–NM–253–AD.

Applicability: Model DC–10–30 airplanes

on which bolt retainers have not been

installed on the engine mount in accordance

with McDonnell Douglas DC–10 Service

Bulletin 71–133, Revision 6, dated June 30,

1992; Model DC–10–10 and –15 airplanes;

and KC–10A (military) airplanes; 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 use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent broken lockwires, which could

result in loosening of the engine mount bolts

and subsequent separation of the engine from

the airplane, accomplish the following:

(a) Within 120 days after the effective date

of this AD, unless accomplished previously

within the last 750 flight hours prior to the

effective date of this AD, perform a visual

inspection to detect broken lockwires on the

forward engine mount bolts on engines 1, 2,

and 3, in accordance with McDonnell

Douglas Alert Service Bulletin DC10–

71A159, Revision 1, dated January 31, 1995.

(1) If no lockwire is found broken, repeat

the inspection thereafter at intervals not to

exceed 750 flight hours.

(2) If any lockwire is found broken, prior

to further flight, check the torque of the bolt,

install a new lockwire, and install a torque

stripe on the bolt, in accordance with the

alert service bulletin. Thereafter at intervals

not to exceed 750 flight hours, perform a

visual inspection to detect misalignment of

the torque stripes, and repeat the inspection

to detect broken lockwires, in accordance

with the alert service bulletin.

(b) Submit a report of findings of broken

lockwires and/or misaligned torque stripes

found during the inspections required by

paragraph (a) of this AD to the Manager, Los

Angeles Aircraft Certification Office, FAA,

Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California

90712; or fax to (310) 627–5210, at the times

specified in either paragraph (b)(1) or (b)(2)

of this AD, as applicable. The report must

include the manufacturer’s fuselage number

of the airplane, number of cycles on the

airplane, torque value of the bolt, and

condition of the lockwire (i.e, broken or

intact). Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

(1) For airplanes on which the inspections

are accomplished after the effective date of

this AD: Submit reports within 30 days after

finding any discrepancy.

(2) For airplanes on which the inspections

have been accomplished prior to the effective

date of this AD: Submit the initial report

within 30 days after the effective date of this

AD, and subsequent reports within 30 days

after finding any discrepancy.

(c) For Model DC–10–30 airplanes and KC–

10A (military) airplanes only: Installation of

retainers on the engine mount bolts in

accordance with Figure 6 of Revision 6 of

McDonnell Douglas DC–10 Service Bulletin

71–133, dated June 30, 1992, constitutes

terminating action for the requirements of

this AD.

(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, 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.

(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.

(f) The inspections shall be done in

accordance with McDonnell Douglas Alert

Service Bulletin DC10–71A159, Revision 1,

dated January 31, 1995. The installation shall

be done in accordance with McDonnell

Douglas DC–10 Service Bulletin 71–133,

Revision 6, dated June 30, 1992. This

incorporation by reference was approved by

the Director of the Federal Register in

accordance with 5 U.S.C. 552(a) and 1 CFR

part 51. Copies may be obtained from

McDonnell Douglas Corporation, P.O. Box

1771, Long Beach, California 90801–1771,

Attention: Business Unit Manager, Technical

Administrative Support, Department L51,

M.C. 2–98. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

FAA, Transport Airplane Directorate, Los

Angeles Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

March 17, 1995.

Issued in Renton, Washington, on February

16, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4379 Filed 3–1–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–14–AD; Amendment

39–9164; AD 95–04–12]

Airworthiness Directives; Airbus Model

A310, A300–600, and A320 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A310, A300–600, and A320 series

airplanes. This action requires

inspections to verify proper installation

of the grille over the air extraction duct

of the lavatory and to detect blockages

in the air extraction duct of the lavatory,

and correction of any discrepancies.

This amendment is prompted by reports

of obstructions in the air extraction

system of the lavatories. The actions

specified in this AD are intended to

prevent obstructions in the air

extraction system of the lavatory, which

may result in the failure of the smoke

detection system to detect smoke in the

lavatories.

DATES: Effective March 17, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of March 17,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

May 1, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

14–AD, 1601 Lind Avenue SW., Renton,

Washington 98055–4056.
11620 Federal Register / Vol. 60, No. 41 / Thursday, March 2, 1995 / Rules and Regulations

The service information referenced in

this AD 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; or at the Office of

the Federal Register, 800 North Capitol

Street NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Stephen Slotte, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: 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,

A300–600, and A320 series airplanes.

The French DGAC advises that there

have been reports of blockage of the air

duct of the air extraction system for the

lavatories on some airplanes.

Investigation into the cause of this

blockage has revealed that either the air

extraction duct may be misaligned with

the hole in the air extraction cover (i.e.,

the duct may be inverted and positioned

180 degrees out of alignment), or the

ceiling louver (grille) that houses the

ceiling light may be installed

improperly (i.e., the light may be

positioned directly over the point of

extraction, which would prevent air

from being extracted).

Each lavatory is equipped with an

extraction system to remove lavatory air

through a duct located above the

lavatory ceiling. This duct is equipped

with a smoke detector to monitor the

extracted air for the presence of smoke.

If this duct is obstructed, the air

extraction system of the lavatories may

be impaired, which could result in the

smoke detection system failing to detect

smoke in the lavatories.

Airbus has issued All Operators Telex

(AOT) 26–12, Revision 1, dated July 4,

1994, which describes procedures for

inspections to verify proper installation

of the grille (ceiling louver) over the air

extraction duct of the lavatory and to

detect blockages in the air extraction

duct of the lavatory. This AOT also

provides instructions for correcting

improperly installed grilles and

blockages in the duct. The French

DGAC classified this AOT as mandatory

and issued French airworthiness

directives 94–169–161(B)R1, dated

September 28, 1994 (for Model A310

and A300–600 series airplanes), and 94–

168–058(B), dated July 20, 1994 (for

Model A320 series airplanes), in order

to assure the continued airworthiness of

these airplanes in France.

This airplane model is manufactured

in France and is 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 French DGAC has kept the FAA

informed of the situation described

above. The FAA has examined the

findings of the French 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.

Since 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, this AD is being issued to

prevent failure of the lavatory smoke

detection system to detect smoke in the

lavatories. This AD requires inspections

to verify proper installation of the grille

over the air extraction duct of the

lavatory and to detect blockages in the

air extraction duct of the lavatory, and

correction of improperly installed grilles

and blockages in the duct. The actions

are required to be accomplished in

accordance with the AOT described

previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–14–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and that it is not a ‘‘significant

regulatory action’’ under Executive

Order 12866. It has been determined

further that this action involves an

emergency regulation under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979). If it is

determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (14 CFR

part 39) as follows:
Federal Register / Vol. 60, No. 41 / Thursday, March 2, 1995 / Rules and Regulations 11621

PART 39—AIRWORTHINESS

DIRECTIVES

1. The authority citation for part 39

continues to read as follows:

Authority: 49 U.S.C. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

95–04–12 Airbus Industrie: Amendment

39–9164. Docket 95–NM–14–AD.

Applicability: Model A310 and A300–600

series airplanes on which Airbus

Modification 10156 has not been

accomplished, and Model A320 series

airplanes on which Airbus Modification

22561 or Airbus Service Bulletin A320–26–

1017 has not been accomplished; certificated

in any category. This AD is not applicable to

airplanes on which the air extraction system

is not configured to detect smoke in the

extracted air. (That is, airplanes that do not

have standard air extraction systems are not

subject to the requirements of this AD.)

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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the lavatory smoke

detection system to detect smoke in the

lavatory, accomplish the following:

(a) Within 450 flight hours after the

effective date of this AD, perform an

inspection of each lavatory to verify proper

installation of the grille over the air

extraction duct of the lavatories, and to

detect blockage in the air extraction duct of

the lavatories, in accordance with Airbus All

Operators Telex (AOT) 26–12, Revision 1,

dated July 4, 1994.

(1) If the grille is found to be properly

installed and if no blockage is found, repeat

the inspection thereafter whenever the cover

over the air extraction duct of the lavatories

or any ceiling louver (grille) of the ceiling

light in the lavatory is removed or replaced

for any reason.

(2) If the grille is found to be improperly

installed and/or if blockage is found, prior to

further flight, correct any discrepancies

found, in accordance with Airbus AOT 26–

12, Revision 1, dated July 4, 1994. Repeat the

inspection thereafter whenever the cover

over the air extraction duct of the lavatories

or any ceiling louver (grille) of the ceiling

light in the lavatory is removed or replaced

for any reason.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

(d) The inspections and correction of

discrepancies shall be done in accordance

with Airbus AOT 26–12, Revision 1, dated

July 4, 1994. This incorporation by reference

was approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

March 17, 1995.

Issued in Renton, Washington, on February

17, 1995.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4544 Filed 3–1–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 92–ANE–34; Amendment 39–

9163; AD 95–04–11]

Airworthiness Directives; Textron

Lycoming ALF502R and ALF502L

Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to Textron Lycoming

ALF502R series turbofan engines, that

currently requires the establishment of a

reduced stress rupture retirement life

limit for certain third stage turbine

disks. This amendment establishes a

new increased stress rupture retirement

life limit for certain third stage turbine

disks used in conjunction with third

stage turbine nozzles that have

improved cooling effectiveness, expands

the applicability by adding the ALF502L

series engines, and establishes other

new reduced stress rupture retirement

life limits. This amendment is prompted

by the introduction of an improved

design third stage turbine nozzle, and a

new reduced stress rupture retirement

life limit for certain third stage turbine

disks on the ALF502L series engines.

The actions specified by this AD are

intended to prevent a total loss of

engine power, inflight engine shutdown,

and possible damage to the aircraft.

DATES: Effective April 3, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 3,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from AlliedSignal Engines, 550 Main

Street, Stratford, CT 06497; (203) 385–

1470. This information may be

examined at the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, 12 New England Executive

Park, Burlington, MA 01803–5299; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7148,

fax (617) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 90–25–02,

Amendment 39–6811 (55 FR 48592,

November 21, 1990), which is

applicable to Textron Lycoming

ALF502R series turbofan engines, was

published in the Federal Register on

March 15, 1993 (58 FR 13711). That

action proposed to expand the

applicability by adding the ALF502L

series. That action would also provide

for increased stress rupture retirement

life limits for certain third stage turbine

disks when used in conjunction with

third stage turbine nozzles that have

improved cooling effectiveness.

On October 28, 1994, AlliedSignal

Inc. purchased the turbine engine

product line of Textron Lycoming, but

as of this date the anticipated name

change on the type certificate for the