Federal Register / Vol. 60, No. 41 / Thursday, March 2, 1995 / Rules and Regulations 11617

(c) Any blade repairs made after the

effective date of this AD shall be

accomplished in accordance with the

procedures specified in Hartzell ASB No.

A196A, dated December 27, 1994.

(d) For propellers that experience a blade

strike, as defined in paragraph (f) of this AD,

after the effective date of this AD, prior to

further flight, accomplish paragraphs (a)(1),

(a)(2), and either (a)(3) or (a)(4) of this AD.

(e) For propellers that have experienced a

blade strike, as defined in paragraph (f) of

this AD, prior to the effective date of this AD,

within the next 100 hours TIS after the

effective date of this AD, accomplish

paragraphs (a)(1), (a)(2), and either (a)(3) or

(a)(4) of this AD.

(f) A blade strike is defined as a propeller

having any blade(s) bent beyond the repair

limits specified in Hartzell Propeller Inc.

Standard Practices Manual 61–01–02,

Revision 1, Pages 1104–1105, dated June

1994.

(g) 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, Chicago

Aircraft Certification Office. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Chicago Aircraft Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Chicago

Aircraft Certification Office.

(h) Except when propellers have

experienced a blade strike, 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 aircraft to a location

where the requirements of this AD can be

accomplished.

(i) The inspections and rework shall be

accomplished in accordance with the

following service documents:

Document No. Pages Date

Hartzell Propeller Inc., ASB No. A196A ............................................................................................................... 1–5 Dec. 27, 1994.

Total pages: 5.

Hartzell Propeller Inc., Standard Practices Manual, 61–01–02, Revision 1 ........................................................ 1104–1105 June 1994.

Total pages: 2.

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 Hartzell Propeller Inc., One Propeller

Place, Piqua, OH 45356–2634; telephone

(513) 778–4200, fax (513) 778–4391. Copies

may be inspected at the FAA, New England

Region, Office of the Assistant Chief Counsel,

12 New England Executive Park, Burlington,

MA; or at the Office of the Federal Register,

800 North Capitol Street, NW., suite 700,

Washington, DC.

(j) This amendment becomes effective on

March 17, 1995.

Issued in Burlington, Massachusetts, on

February 7, 1995.

Donald F. Perrault,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–4248 Filed 3–1–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 94–NM–253–AD; Amendment

39–9159; AD 95–04–07]

Airworthiness Directives; McDonnell

Douglas Model DC–10–10, –15, and –30

Airplanes, and KC–10A (Military)

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 McDonnell

Douglas Model DC–10 series airplanes

and KC–10A (military) airplanes. This

action requires inspections to determine

the condition of the lockwires on the

forward engine mount bolts and

correction of any discrepancies found.

This action also provides for

termination of the inspections for some

airplanes by installing retainers on the

bolts. This amendment is prompted by

reports of stretched or broken lockwires

on the forward engine mount bolts. The

actions specified in this AD are

intended to prevent broken lockwires,

which could result in loosening of the

engine mount bolts, and subsequent

separation of the engine from the

airplane.

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. 94–NM–

253–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD 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.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the 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.

FOR FURTHER INFORMATION CONTACT:

Maureen A. Moreland, Aerospace

Engineer, Airframe Branch, ANM–121L,

FAA, Transport Airplane Directorate,

Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712; telephone

(310) 627–5238; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: On

October 10, 1985, the FAA issued AD

85–22–01, amendment 39–5157, (50 FR

42153, October 18, 1985) applicable to

certain McDonnell Douglas Model DC–

10–10, –15, –30, and –40 airplanes, and

KC–10A (military) airplanes. That AD

requires repetitive inspections of the

engine-to-pylon forward and aft mount

and the engine mount bolts; and

replacement of the bolts and nuts,

torque check of the bolts, and

installation of a torque stripe on the

bolts, if necessary. That AD provided for

termination of the inspections by

replacing the engine mount bolts with

bolts having a lockwire hole in the bolt

head, installing tabs with a lockwire

hole, and installing lockwires.

Since the issuance of that AD, the

FAA has received reports of broken or

stretched lockwires on the forward

engine mount bolts on several Model

DC–10–30 airplanes on which the

terminating actions described in AD 85–

22–01 had been accomplished.

Investigation has revealed that these

lockwires may have stretched and

eventually broken because the foward

engine mount bolts had loosened.

McDonnell Douglas has developed a

bolt retainer that will prevent these

bolts from loosening from the engines of

Model DC–10–30 airplanes and KC–10A

(military) airplanes.

Additionally, the FAA has received

reports of loose bolts on the engine
11618 Federal Register / Vol. 60, No. 41 / Thursday, March 2, 1995 / Rules and Regulations

mounts of Model DC–10–10 airplane

engines. However, McDonnell Douglas

has not yet developed a bolt retainer for

Model DC–10–10 or –15 airplanes, or

KC–10A airplanes.

Broken lockwires, if not corrected,

could result in loosening of the engine

mount bolts and subsequent separation

of the engine from the airplane.

The lockwires on the forward engine

mount bolts of Model DC–10–30

airplanes are similar to those installed

on Model DC–10–10 and –15 airplanes,

and KC–10A airplanes. Therefore, the

FAA finds that Model DC–10–10 and

–15 airplanes, and KC–10A airplanes

are also subject to the same unsafe

condition.

The FAA has reviewed and approved

McDonnell Douglas Alert Service

Bulletin DC10–71A159, Revision 1,

dated January 31, 1995, which describes

procedures for repetitive visual

inspections to detect broken lockwires

on the forward engine mount bolts on

engines 1, 2, and 3. If any broken

lockwire is found, the service bulletin

describes procedures to check the

torque of the bolt, to install a new

lockwire, and to install a torque stripe

on the bolt. This service bulletin also

describes procedures for subsequent

visual inspections to detect

misalignment of the torque stripe.

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design, this AD is being issued to

prevent broken lockwires, which could

result in loosening of the engine mount

bolts and subsequent separation of the

engine from the airplane. This AD

requires visual inspections to determine

the condition of the lockwires on the

forward engine mount bolts on engines

1, 2, and 3, and correction of

discrepancies found. The actions are

required to be accomplished in

accordance with the alert service

bulletin described previously.

The required compliance time of 120

days is usually sufficient to allow for a

brief comment period before adoption of

a final rule. In this AD, however, that

compliance time was selected because

of the degree of urgency associated with

addressing the subject unsafe condition

and the practical aspects of performing

the inspection within a maximum

interval of time allowable for all affected

airplanes to continue to operate without

compromising safety. Further, the FAA

took into account the 6-month

compliance time recommended by the

manufacturer, as well as the number of

days required for the rulemaking

process; in consideration of these

factors, the FAA finds that 120 days

after the effective date of this rule will

fall approximately at the same time as

that recommended by the manufacturer.

This AD also requires that operators

report the results of the visual

inspections to the FAA. The intent of

these reports is to enable the FAA to

determine how widespread the problem

of broken lockwires may be in the

affected fleet. Based on the results of

these reports, further corrective action

may be warranted.

Since retainers have been developed

only for Model DC–10–30 airplanes and

KC–10A airplanes, this AD also

provides for the termination of the

visual inspections by installing retainers

on the engine mount bolts on Model

DC–10–30 airplanes and KC–10A

airplanes in accordance with Revision 6

of McDonnell Douglas DC–10 Service

Bulletin 71–133, dated June 30, 1992.

As a result of recent communications

with the Air Transport Association

(ATA) of America, the FAA has learned

that, in general, some operators may

misunderstand the legal effect of AD’s

on airplanes that are identified in the

applicability provision of the AD, but

that have been altered or repaired in the

area addressed by the AD. The FAA

points out that all airplanes identified in

the applicability provision of an AD are

legally subject to the AD. If an airplane

has been altered or repaired in the

affected area in such a way as to affect

compliance with the AD, the owner or

operator is required to obtain FAA

approval for an alternative method of

compliance with the AD, in accordance

with the paragraph of each AD that

provides for such approvals. A note has

been included in this rule to clarify this

long-standing requirement.

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 94–NM–253–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
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.