19344 Federal Register / Vol. 60, No. 74 / Tuesday, April 18, 1995 / Rules and Regulations

There are approximately 350 engines

with the affected serial numbered disks

in the worldwide fleet. The FAA

estimates that 175 engines installed on

aircraft of U.S. registry will be affected

by this AD, that it will take

approximately 10 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 $18,000 per engine.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $3,255,000.

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:

95–07–02 AlliedSignal Inc.: Amendment

39–9181. Docket 94–ANE–42.

Applicability: AlliedSignal Inc. (formerly

Garrett Turbine Engine Company) TFE731–3,

–3A, –3AR, –3B, –3BR, and –3R turbofan

engine models installed on but not limited to

Avions Marcel Dassault Falcon 50, Lockheed

1329–23, –25 series (731 Jetstar, Jetstar II),

Israel Aircraft Industries (IAI) Ltd. 1124

(Westwind), Raytheon Corporate Jets Inc.

(formerly British Aerospace) (BAe) DH/HS/

BH 125 series, Learjet 55 series, Cessna 650

Citation III, VI, Sabreliner NA–265 series

(Sabreliner 65). This airworthiness directive

(AD) is not applicable to TFE731–3A–300G

and TFE731–3AR–200G engines installed on

IAI 1125 Westwind Astra aircraft.

Compliance: Required as indicated, unless

accomplished previously.

To prevent a low pressure turbine (LPT)

disk web separation, which may result in an

uncontained engine failure and damage to

the aircraft, accomplish the following:

(a) Remove from service first and second

stage LPT disks, with Part Numbers (P/N)

3072351–(), 3072542–(), 3073113–(), and

3073114–(), where () denotes any dash

number, identified by serial number in the

Compliance Sections of AlliedSignal

Aerospace Alert Service Bulletin (ASB) No.

TFE731–A72–3544, dated October 8, 1993,

and AlliedSignal Aerospace ASB No.

TFE731–A72–3557, dated May 12, 1994,

within 1,500 hours time in service (TIS) after

the effective date of this AD, or at the next

removal of the LPT assembly, whichever

occurs first, in accordance with the

Accomplishment Instructions of AlliedSignal

Aerospace ASB No. TFE731–A72–3544,

dated October 8, 1993, and AlliedSignal

Aerospace ASB No. TFE731–A72–3557,

dated May 12, 1994, and replace with

serviceable disks.

(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. The

request should be forwarded through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Los Angeles 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 Los Angeles

Aircraft Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(d) The removal and replacement of the

affected disks shall be done in accordance

with the following AlliedSignal Aerospace

ASB’s:

Document No. Pages Date

ASB No. TFE731–A72–

3544.

1–10 Oct. 8,

1993.

Total Pages: 10.

ASB No. TFE731–A72–

3557.

1–12 May 12,

1994.

Total Pages: 12.

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 AlliedSignal Inc., Aviation Services

Division, Data Distribution, Dept. 6403/2102–

201, P.O. Box 29003, Phoenix, AZ 85038–

9003; telephone (602) 365–2548, fax (602)

365–2210. 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.

(e) This amendment becomes effective on

June 19, 1995.

Issued in Burlington, Massachusetts, on

March 22, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–8827 Filed 4–17–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 94–NM–152–AD; Amendment

39–9194; AD 95–08–05]

Airworthiness Directives; British

Aerospace Model BAe 146–100A,

–200A, and –300A, and Model Avro

146–RJ70A, –RJ85A, and –RJ100A

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe 146–100A, –200A, and

–300A series airplanes, that currently

requires repetitive inspections of the

attachment bolts and nuts in the rear

spar root joint attachment fittings at

wing rib 2 for integrity of nuts, tightness

of bolts, and/or fuel leaks; and repair, if

necessary. That AD was prompted by

fuel leaks from bolt positions on the rear

spar attachment fitting at wing rib 2.

This amendment provides for an

optional terminating modification for

the repetitive inspections, and expands

the applicability of the existing AD to

include additional airplanes. The

actions specified by this AD are

intended to prevent fuel leaks and a

subsequent fire.

DATES: Effective on May 18, 1995.
Federal Register / Vol. 60, No. 74 / Tuesday, April 18, 1995 / Rules and Regulations 19345

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 18,

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)

by superseding AD 90–08–15,

amendment 39–6577 (55 FR 13757,

April 12, 1990), which is applicable to

certain British Aerospace Model BAe

146–100A, –200A, and –300A series

airplanes, was published in the Federal

Register on November 29, 1994 (59 FR

60924). The action proposed to

supersede AD 90–08–15 to continue to

require repetitive visual inspections for

integrity of nuts, tightness of bolts, and/

or fuel leaks of the outboard vertical row

of fasteners at the left- and right- hand

of the rear spar root joint attachment

fittings. The action proposed to provide

for an optional terminating modification

for the repetitive inspections.

Additionally, the action proposed to

expand the applicability of the existing

AD to include additional airplanes.

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 supports the

proposed rule.

One commenter requests that NOTE 1

of the proposal be revised to allow

carriers with Special Federal Aviation

Regulation (SFAR) 36 authority to make

a determination whether a repair

modification or alteration provides an

equivalent level of safety. The FAA does

not concur. As discussed in the

proposal, the referenced note is merely

an explanation of the legal effect of the

applicability statement (i.e., all

airplanes identified in that statement are

subject to the requirements of the AD).

Since the note is simply informational,

it cannot be revised to ‘‘allow’’ operators

to make determinations that they are not

otherwise allowed to make. The note

directs operators (that have airplanes

with altered or repaired configurations)

to the provisions of paragraph (d) of the

AD, which allows them to obtain

approval of an alternative method of

compliance (AMOC) with the AD. The

FAA infers that the commenter is

actually requesting that operators

holding SFAR 36 authorizations be

allowed, in essence, to approve their

own AMOC’s. The FAA has assigned a

task to the Aviation Rulemaking

Advisory Committee (ARAC) to review

the AMOC process and to recommend

improvements to it. The issue of

whether the FAA should delegate its

authority to approve AMOC’s is being

addressed in that context. The FAA will

consider ARAC’s recommendations

once they are received. Therefore, the

FAA considers any action on this

subject to be premature until ARAC has

submitted its recommendations.

The FAA has reviewed the

applicability of the proposal and has

determined that referencing both British

Aerospace Service Bulletin SB 57–33,

dated August 31, 1989, and Avro

International Aerospace Service Bulletin

S.B. 57–33, Revision 3, dated September

16, 1994, is unnecessary. Revision 3 of

the Avro service bulletin includes the

same airplanes listed in the effectivity

listing of the original version of that

service bulletin, as well as those listed

in the British Aerospace service

bulletin. Therefore, the FAA has revised

the applicability statement of the final

rule to reference only Revision 3 of the

Avro service bulletin.

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 11 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

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 $1,320, or $120 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

removing amendment 39–6577 (55 FR

13757, April 12, 1990), and by adding

a new airworthiness directive (AD),

amendment 39–9194, to read as follows:

95–08–05 British Aerospace Regional

Aircraft Limited, Avro International

Aerospace Division (Formerly British

Aerospace, plc; British Aerospace

Commercial Aircraft Limited):

Amendment 39–9194. Docket 94–NM–

152–AD. Supersedes AD 90–08–15,

Amendment 39–6577.

Applicability: Model British Aerospace

Model BAe 146–100A, –200A, and –300A
19346 Federal Register / Vol. 60, No. 74 / Tuesday, April 18, 1995 / Rules and Regulations

series airplanes, and Model Avro 146–RJ70A,

–RJ85A, and –RJ100A series airplanes; as

listed in Avro International Aerospace

Service Bulletin S.B. 57–33, Revision 3,

dated September 16, 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 (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 fuel leaks and a subsequent fire,

accomplish the following:

(a) For airplanes listed in British Aerospace

Service Bulletin SB 57–33, dated August 31,

1989: Within 12 months after May 21, 1990

(the effective date of AD 90–08–15,

amendment 39–6577), visually inspect for

integrity of nuts and tightness of bolts, and/

or fuel leaks of the outboard vertical row of

fasteners at the left- and right-hand of the

rear spar root joint attachment fittings, in

accordance with British Aerospace Service

Bulletin 57–33, dated August 31, 1989;

Revision 1, dated October 29, 1993; Revision

2, dated February 16, 1994; or Revision 3,

dated September 16, 1994. Repeat the

inspection thereafter at intervals not to

exceed 4,000 landings.

(1) If no defects are found, prior to further

flight, reinstall the left- and right-hand wingto-fuselage fairing panels in accordance with

the service bulletin.

(2) If any defect is found, prior to further

flight, repair suspect and leaking fasteners, in

accordance with the service bulletin.

(b) For airplanes listed in Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 3, dated September 16, 1994,

and not subject to paragraph (a) of this AD:

Within 12 months after the effective date of

this AD, visually inspect for integrity of nuts

and tightness of bolts, and/or fuel leaks of the

outboard vertical row of fasteners at the leftand right-hand of the rear spar root joint

attachment fittings, in accordance with Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 1, dated October 29, 1993;

Revision 2, dated February 16, 1994; or

Revision 3, dated September 16, 1994. Repeat

the inspection thereafter at intervals not to

exceed 4,000 landings.

(1) If no defects are found, prior to further

flight, reinstall the left- and right-hand wingto-fuselage fairing panels in accordance with

the service bulletin.

(2) If any defect is found, prior to further

flight, repair suspect and leaking fasteners in

accordance with the service bulletin.

(c) Modification of the rear spar root joint

attachment fittings at wing rib 2 in

accordance with Avro International

Aerospace Service Bulletin S.B. 57–33,

Revision 1, dated October 29, 1993; Revision

2, dated February 16, 1994; or Revision 3,

dated September 16, 1994; constitutes

terminating action for the repetitive visual

inspections required by 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,

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.

(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 actions done in accordance with

British Aerospace Service Bulletin SB 57–33,

dated August 31, 1989, including Appendix

A; Avro International Aerospace Service

Bulletin S.B. 57–33, Revision 1, dated

October 29, 1993; Avro International

Aerospace Service Bulletin S.B. 57–33,

Revision 2, dated February 16, 1994; or Avro

International Aerospace Service Bulletin S.B.

57–33, Revision 3, dated September 16, 1994;

as applicable. Revision 3 of Avro

International Aerospace Service Bulletin S.B.

57–33 contains the following list of effective

pages:

Page No.

Revision

level

shown on

page

Date shown

on page

1–3 ....................... 3 Sept. 16,

1994.

4–6 ....................... 2 February 16,

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 British Aerospace Holdings, Inc., Avro

International Aerospace Division, P.O. Box

16039, Dulles International Airport,

Washington, DC 20041–6039. 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.

(g) This amendment becomes effective on

May 18, 1995.

Issued in Renton, Washington, on April 5,

1995.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–8825 Filed 4–17–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–SW–06–AD; Amendment

39–9201; AD 95–08–12]

Airworthiness Directives; Eurocopter

Deutschland GmbH (ECD) Model MBBBK 117 A–1, A–3, A–4, B–1, B–2, and

C–1 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter Deutschland

GmbH (ECD) Model MBB-BK 117 A–1,

A–3, A–4, B–1, B–2, and C–1

helicopters, that requires a modification

of the latches on the transmission and

engine cowling access doors. This

amendment is prompted by five

occurrences of an engine or

transmission cowling access door

becoming loose in flight. The actions

specified by this AD are intended to

prevent the transmission and engine

cowling access doors from opening in

flight, being struck by the main rotor

blade, and subsequently, separating

from the helicopter and being ingested

by the main rotor or tail rotor system

resulting in a loss of control of the

helicopter.

DATES: Effective May 23, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 23,

1995.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005. This information may be

examined at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Richard Monschke, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Standards Staff, 2601 Meacham Blvd.,

Fort Worth, Texas 76137, telephone

(817) 222–5116, fax (817) 222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal