Federal Register / Vol. 60, No. 105 / Thursday, June 1, 1995 / Rules and Regulations 28527

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:

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:

95–11–12 McDonnell Douglas: Amendment

39–9245. Docket 94–NM–194–AD.

Applicability: Model DC–9–10, –20, –30,

–40, and –50 series airplanes; Model DC–9–

81 (MD–81), DC–9–82 (MD–82), DC–9–83

(MD–83), and DC–9–87 (MD–87) series

airplanes; Model MD–88 airplanes; and C–9

(military) series airplanes; as listed in

McDonnell Douglas DC–9 Service Bulletin

24–150, dated March 28, 1994; 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 (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 ensure replacement of the emergency

power switch that have reached the

maximum life limit, accomplish the

following:

(a) Prior to the accumulation of 3 years

since installation of the emergency power

switch in the overhead switch panel, or

within 12 months after the effective date of

this AD, whichever occurs later, replace the

emergency power switch with a new switch

in accordance with the procedures specified

in McDonnell Douglas DC–9 Service Bulletin

24–150, dated March 28, 1994, or Revision 1,

dated April 7, 1995. Thereafter, replace the

emergency power switch at intervals not to

exceed 3 years.

(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.

(d) The replacement shall be done in

accordance with McDonnell Douglas DC–9

Service Bulletin 24–150, dated March 28,

1994; or McDonnell Douglas DC–9 Service

Bulletin 24–150, Revision 1, dated April 7,

1995. 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, 3855

Lakewood Boulevard, Long Beach, California

90846, Attention: Technical Publications

Business Administration, Department C1–

L51 (2–60). Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 3960

Paramount Boulevard, Lakewood, California;

or at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(e) This amendment becomes effective on

July 3, 1995.

Issued in Renton, Washington, on May 22,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–12951 Filed 5–31–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–NM–96–AD; Amendment

39–9246; AD 95–11–13]

Airworthiness Directives; McDonnell

Douglas Model MD–11 Series

Airplanes Equipped With Pratt &

Whitney Model PW4460 and PW4462

Engines

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 MD–11 series airplanes.

This action requires a visual inspection

to detect cracks or discrepancies in the

aft mount beam assembly of the engines;

and replacement of the cracked or

discrepant aft mount beam assembly

with a new assembly, or a previously

inspected and re-identified assembly.

This amendment is prompted by reports

of cracking in a certain aft mount beam

assembly on Airbus Model A310 series

airplanes. The actions specified in this

AD are intended to prevent cracks in the

aft mount beam assembly of the engines,

which could result in loss of the

capability of the aft mount beam

assembly to support engine loads, and

possible separation of the engine from

the airplane.

DATES: Effective June 16, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 16,

1995.

Comments for inclusion in the Rules

Docket must be received on or before

July 31, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

96–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

The service information referenced in

this AD 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; or at the FAA, Los Angeles

Aircraft Certification Office, Transport

Airplane Directorate, 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:

Wahib Mina, Aerospace Engineer,

Airframe Branch, ANM–120L, FAA, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712; telephone (310) 627–

5324; fax (310) 627–5210.

SUPPLEMENTARY INFORMATION: The FAA

has received reports of cracking in an aft

mount beam assembly having part

number (P/N) 221–0261–501 installed

on Airbus Model A310 series airplanes.

Metallurgical analysis and close

examination of the cracked aft mount

beam assembly has indicated this

cracking is the result of physical defects,

which were caused during the forging

process by one supplier. Cracks in the

aft mount beam assembly of the engines,

if not detected and corrected in a timely
28528 Federal Register / Vol. 60, No. 105 / Thursday, June 1, 1995 / Rules and Regulations

manner, could result in loss of the

capability of the aft mount beam

assembly to support engine loads, and

possible separation of the engine from

the airplane.

Aft mount beam assemblies having P/

N 221–0261–501 are also installed on

McDonnell Douglas Model MD–11

series airplanes equipped with Pratt &

Whitney PW4460 and PW4462 engines.

The FAA has determined that these

airplanes are also subject to the

addressed unsafe condition.

The FAA may consider similar

rulemaking action that is applicable to

Airbus Model A310 series airplanes on

which the suspect mount beam

assembly also may be installed.

The FAA has reviewed and approved

McDonnell Douglas Alert Service

Bulletin MD11–71A073, Revision 1,

dated May 16, 1995, which describes

procedures for a one-time visual

inspection to detect cracks or

discrepancies in the aft mount beam

assembly, P/N 221–0261–501, of engine

numbers 1, 2, and 3. This alert service

bulletin also describes procedures for

replacement of the cracked or

discrepant aft mount beam assembly

with a new assembly having P/N 221–

0261–503, or a previously inspected and

re-identified assembly having P/N 221–

0261–501.

Since an unsafe condition has been

identified that is likely to exist or

develop on certain other McDonnell

Douglas Model MD–11 series airplanes

of the same type design, this AD is being

issued to prevent loss of the capability

of the aft mount beam assembly to

support engine loads, and possible

separation of the engine from the

airplane. This AD requires a one-time

visual inspection to detect cracks or

discrepancies in the aft mount beam

assembly of the engines; and

replacement of the cracked or

discrepant aft mount beam assembly

with a certain new assembly, or a

certain previously inspected and reidentified assembly. The actions are

required to be accomplished in

accordance with the alert service

bulletin described previously.

This AD also requires that operators

report results of inspection findings,

positive or negative, to the FAA.

The FAA is considering further

rulemaking action to require fluorescent

penetrant and eddy current inspections

of the aft mount beam assembly, P/N

221–0261–501, of the engines within

4,000 flight cycles after accomplishing

the visual inspection required by this

AD. However, the proposed compliance

time for the one-time visual inspection

is sufficiently long so that notice and

time for public comment would not be

impracticable.

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 added to this final 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 95–NM–96–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:

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:

95–11–13 McDonnell Douglas: Amendment

39–9246. Docket 95–NM–96–AD.
Federal Register / Vol. 60, No. 105 / Thursday, June 1, 1995 / Rules and Regulations 28529

Applicability: Model MD–11 series

airplanes, equipped with Pratt & Whitney

Model PW4460 and PW4462 engines; as

listed in McDonnell Douglas Alert Service

Bulletin MD11–71A073, Revision 1, dated

May 16, 1995; 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 (d) 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 loss of the capability of the aft

mount beam assembly to support engine

loads, and possible separation of the engine

from the airplane, accomplish the following:

(a) Within 60 days after the effective date

of this AD, perform a visual inspection to

detect cracks or discrepancies in the aft

mount beam assembly, part number (P/N)

221–0261–501, of engine numbers 1, 2, and

3, in accordance with McDonnell Douglas

Alert Service Bulletin MD11–71A073,

Revision 1, dated May 16, 1995.

(1) If no cracks or discrepancies are

detected, no further action is required by this

AD.

(2) If any crack or discrepancy is detected,

prior to further flight, replace the cracked or

discrepant aft mount beam assembly with a

new assembly having P/N 221–0261–503, or

an assembly having P/N 221–0261–501 that

has been previously inspected and reidentified, in accordance with paragraph

3.B., Phase 2, of the Accomplishment

Instructions of the alert service bulletin.

Replacement shall be accomplished in

accordance with the procedures specified in

the alert service bulletin.

(b) Within 10 days after accomplishing the

inspection required by this AD, report

inspection results, positive or negative, to the

Manager, Los Angeles Aircraft Certification

Office (ACO), FAA, Transport Airplane

Directorate, 3960 Paramount Boulevard,

Lakewood, California 90712; fax (310) 627–

5210. 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.

(c) As of the effective date of this AD, no

person shall install an aft mount beam

assembly, P/N 221–021–501, on any airplane,

unless it has been previously inspected and

re-identified in accordance with the

paragraph 3.B., Phase 2, of the

Accomplishment Instructions of McDonnell

Douglas Alert Service Bulletin MD11–

71A073, Revision 1, dated May 16, 1995.

(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 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 inspection, replacement, and reidentification shall be done in accordance

with McDonnell Douglas Alert Service

Bulletin MD11–71A073, Revision 1, dated

May 16, 1995. 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, 3855 Lakewood Boulevard,

Long Beach, California 90846, Attention:

Technical Publications Business

Administration, Department C1–L51 (2–60).

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

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

FAA, Los Angeles Aircraft Certification

Office, Transport Airplane Directorate, 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

June 16, 1995.

Issued in Renton, Washington, on May 22,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–12950 Filed 5–31–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 90–CE–67–AD; Amendment 39–

9250; AD 95–11–17]

Airworthiness Directives; Jetstream

Aircraft Limited (Formerly British

Aerospace, Regional Aircraft Limited)

Jetstream Models 3101 and 3201

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 90–13–12,

which currently requires modifying the

airplane electrical system and revising

the emergency procedures section of the

Airplane Flight Manual (AFM) on

certain Jetstream Aircraft Limited (JAL)

Jetstream Models 3101 and 3201

airplanes. This action retains the

requirements of AD 90–13–12 for those

airplanes that do not have modified

inverters installed and the inverted

transfer function restored. The Federal

Aviation Administration (FAA) has

determined that installing modified

inverters along with restoring the

inverter transfer function corrects the

problems in the power supply

addressed by AD 90–13–12. The actions

specified by this AD are intended to

prevent alternating current system

failures, which, if not detected and

corrected, could result in damage to the

airplane navigational systems.

DATES: Effective July 19, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 19,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Jetstream Aircraft Limited, Manager

Product Support, Prestwick Airport,

Ayrshire, KA9 2RW Scotland; telephone

(44–292) 79888; facsimile (44–292)

79703; or Jetstream Aircraft Inc.,

Librarian, P.O. Box 16029, Dulles

International Airport, Washington, DC

20041–6029; telephone (703) 406–1161;

facsimile (703) 406–1469. This

information may also be examined at

the FAA, Central Region, Office of the

Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri

64106; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Raymond A. Stoer, Program Officer,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

513.3830; facsimile (322) 230.6899; or

Mr. Sam Lovell, Project Officer, Small

Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

certain JAL Models 3101 and 3201

airplanes was published in the Federal

Register on February 10, 1995 (60 FR

7922). The action proposed to supersede

AD 90–13–12 with a new AD that would

(1) retain the requirements of modifying