Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12411

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:

95–04–08 Boeing: Amendment 39–9160.

Docket 94–NM–153–AD

Applicability: Model 747–300 and –400

series airplanes equipped with BFGoodrich

stretched upper deck evacuation slides, part

number (P/N) 7A1323–1, –2, –3, –4, –105,

–106, –107, –108, –109, or –110; 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 prevent loss of air pressure or noninflation of the inflation tubes of an

evacuation slide, which could impede the

evacuation of passengers from the airplane

during an emergency, accomplish the

following:

(a) Within 36 months after the effective

date of this AD, modify the BFGoodrich

stretched upper deck evacuation slide, P/N

7A1323-( ), in accordance with the

Accomplishment Instructions of BFGoodrich

Service Bulletin 7A1323–25–266, Revision 1,

dated September 30, 1994.

Note 2: Installation of the ‘‘product

improvements,’’ specified in paragraph 2.J. of

the Accomplishment Instructions of the

service bulletin, is not required by this AD.

(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 3: 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 modification shall be done in

accordance with BFGoodrich Service

Bulletin 7A1323–25–266, Revision 1, dated

September 30, 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 BFGoodrich Company,

Aircraft Evacuation Systems, Dept. 7916,

Phoenix , Arizona 85040. 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

April 6, 1995.

Issued in Renton, Washington, on February

16, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4378 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 93–ANE–40; Amendment 39–

9154; AD 95–04–02]

Airworthiness Directives; Rolls-Royce,

plc RB211–524 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Rolls-Royce, plc

RB211–524 series turbofan engines, that

requires a one-time modification of the

nozzle guide vane (NGV) assembly to

incorporate vane core reinforcement

inserts which would prevent release of

the stage 2 NGV seal ring, rotor contact,

and severance of the rotor drive arm.

This amendment is prompted by a

report of an uncontained stage 1 low

pressure turbine failure. The actions

specified by this AD are intended to

prevent release of the stage 2 NGV seal

ring, which could result in an

uncontained engine failure.

DATES: Effective May 8, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 8,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from Rolls-Royce, plc, P.O. Box 31,

Derby, England DE2 8BJ; telephone 44–

332–242424, 44–332–249936. 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; 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) to

include an airworthiness directive (AD)

that is applicable to certain Rolls-Royce,

plc (R–R) RB211–524 series turbofan

engines was published in the Federal

Register on October 4, 1993 (58 FR

51585). That action proposed to require

a one-time modification of the nozzle

guide vane (NGV) assembly to

incorporate vane core reinforcement

inserts which would prevent release of

the stage 2 NGV seal ring, rotor contact,

and severance of the rotor drive arm in

accordance with R–R Mandatory Service

Bulletin (SB) No. RB.211–72–9672,

Revision 1, dated November 6, 1992.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter concurs with the rule

as proposed.

One commenter states that the

proposed rule should provide separate

compliance times for spare engines. The

commenter further states that the

proposed rule notes that no U.S. registry

engines would be affected. The

commenter has one affected spare

engine, and states that an acceptable
12412 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

level of safety would be maintained

provided the spare engine is modified

within 20 months of installation. The

FAA concurs in part. The FAA has

revised the economic analysis of this

final rule to include the one domestic

spare engine. However, the FAA does

not concur with the proposal to require

modifying spare engines within 20

months after installation on Lockheed

L–1011 aircraft, or at the next shop visit.

The FAA has determined that the

acceptable level of safety maintained by

this AD is based on total fleet

compliance within a finite period after

AD issuance. The commenter’s proposal

to modify spare engines within 20

months after installation or at the next

shop visit could allow indefinite

operation of unmodified engines, if an

engine were removed for use as a spare

engine and subsequently installed

without undergoing a shop visit.

Therefore, the FAA concludes that the

compliance timetable originally

provided in the NPRM is appropriate to

maintain an acceptable level of safety.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

There are approximately 300 R–R

RB211–524 series turbofan engines of

the affected design in the worldwide

fleet. The FAA estimates that 1 spare

engine of U.S. registry will be affected

by this AD, that it will take

approximately 37 work hours per engine

to accomplish the required actions, and

that the average labor rate is $60 per

work hour. Required parts will cost

approximately $2,420 per engine. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $4,640.

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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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:

95–04–02 Rolls-Royce, plc: Amendment

39–9154. Docket 93–ANE–40.

Applicability: Rolls-Royce, plc (R–R)

Models RB211–524B–02, –524B–B–02,

–524B3–02, –524B2–19, –524B2–B–19,

–524C2–19, and –524C2–B–19 turbofan

engines, installed on but not limited to

Boeing 747 series and Lockheed L–1011

series aircraft.

Compliance: Required as indicated, unless

accomplished previously.

To prevent release of the stage 2 nozzle

guide vane (NGV) seal ring, which could

result in an uncontained engine failure,

accomplish the following:

(a) For engines installed on Boeing 747

series aircraft, modify the NGV assembly in

accordance with R–R Mandatory Service

Bulletin (SB) No. RB.211–72–9672, Revision

1, dated November 6, 1992, at the next shop

visit, but not later than 9 months after the

effective date of this airworthiness directive

(AD), whichever occurs first.

(b) For engines installed on Lockheed L–

1011 series aircraft, modify the NGV

assembly in accordance with R–R Mandatory

SB No. RB.211–72–9672, Revision 1, dated

November 6, 1992, at the next shop visit, but

not later than 20 months after the effective

date of this AD, whichever occurs first.

(c) For the purpose of this AD, a shop visit

is defined as an engine removal where engine

maintenance entails separation of pairs of

mating engine flanges or the removal of a

disk, hub, or spool.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(f) The modification shall be done in

accordance with the following SB:

Document No. Pages Revision Date

R–R SB No. RB.211–72–9672 ........................................................................................................................ 1–31 1 Nov. 6, 1992.

R–R SB Supplement ........................................................................................................................................ 1–2 1 Nov. 6, 1992.

Total pages 33

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 Rolls-Royce, plc, P.O. Box 31, Derby,

England DE2 8BJ; telephone 44–332–242424,

fax 44–332–249936. 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.

(g) This amendment becomes effective on

May 8, 1995.
Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12413

Issued in Burlington, Massachusetts, on

February 15, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–4545 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 94–NM–157–AD; Amendment

39–9158; AD 95–04–06]

Airworthiness Directives; British

Aerospace Model Avro 146–RJ Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all British Aerospace

Model Avro 146–RJ series airplanes,

that requires inspections to detect

cracking of the upper main fitting of the

nose landing gear (NLG), and

replacement or repair of cracked parts.

This amendment is prompted by reports

of cracking of the upper main fitting of

the NLG. The actions specified by this

AD are intended to prevent failure of the

main fitting, which could lead to

collapse of the NLG during landing.

DATES: Effective on April 6, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 6,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from British Aerospace Holdings, Inc.,

Avro International Aerospace Division,

P.O. Box 16039, Dulles International

Airport, Washington DC 20041–6039.

This information may be examined at

the Federal Aviation Administration

(FAA), Transport Airplane Directorate,

Rules Docket, 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:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all British

Aerospace Model Avro 146–RJ series

airplanes was published in the Federal

Register on November 7, 1994 (59 FR

55380). That action proposed to require

repetitive eddy current or ultra high

sensitivity penetrant inspections, and

replacement or repair of cracked parts.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

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 requirement.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

The FAA estimates that 3 airplanes of

U.S. registry will be affected by this AD,

that it will take approximately 2.5 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $450, or $150 per airplane.

The total cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it 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:

95–04–06 British Aerospace Regional

Aircraft Limited, Avro International

Aerospace Division (Formerly British

Aerospace, plc; British Aerospace

Commercial Aircraft, Limited):

Amendment 39–9158. Docket 94–NM–

157–AD.

Applicability: All Model Avro 146–RJ

series 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