12408 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

The FAA estimates that 3 airplanes of

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

that it will take approximately 1.5 work

hours per airplane to accomplish the

required actions, and that the average

labor rate is $60 per work hour.

Required parts will cost approximately

$250 per airplane. Based on these

figures, the total cost impact of the AD

on U.S. operators is estimated to be

$1,020, or $340 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:

95–04–04 British Aerospace Regional

Aircraft Limited, Avro International

Aerospace Division (Formerly British

Aerospace, PLC; British Aerospace

Commercial Aircraft Limited):

Amendment 39–9156. Docket 94–NM–

132–AD.

Applicability: Model Avro 146–RJ70A and

–RJ85A airplanes, as listed in Avro

International Aerospace Service Bulletin 49–

40, Revision 1, dated March 17, 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 prevent loss of electrical power to the

auxiliary power unit (APU), accomplish the

following:

(a) Within 5 months after the effective date

of this AD, perform a detailed visual

inspection to identify the cable terminals

fitted to cables KA47 and KA48 in the APU

starter circuit at terminal block KA9, in

accordance with Avro International

Aerospace Service Bulletin S.B. 49–40,

Revision 1, dated March 17, 1994. If the cable

terminals are identified as part number (P/N)

S1007–042, prior to further flight, remove the

cable terminals and install new cable

terminals having P/N S1006–040, in

accordance with the service bulletin.

(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 inspection, removal, and

installation shall be done in accordance with

Avro International Aerospace Service

Bulletin S.B. 49–40, Revision 1, dated March

17, 1994, which contains the following list of

effective pages:

Page No.

Revision

level

shown on

page

Date shown on

page

1– ................. 1– ............ Mar. 17, 1994.

2–4– ............. Original .... Feb. 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.

(e) This amendment becomes effective on

April 6, 1995.

Issued in Renton, Washington, on February

15, 1995.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–4255 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–CE–10–AD; Amendment 39–

9161; AD 95–04–09]

Airworthiness Directives; Pilatus

Britten-Norman BN2A, BN2B, and

BN2T Islander Series and BN2A Mk III

Trislander Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Pilatus Britten-Norman

BN2A, BN2B, and BN2T Islander and

BN2A Mk III Trislander series airplanes

that are equipped with a nose wheel

steering disconnect system with either a

Modification NB/M/503 or Modification

NB/M/733 nose undercarriage unit. This

action requires repetitively inspecting

the nose wheel steering drive ring for

cracks, and replacing any cracked drive

ring. A report of the rudder pedals

jamming in the central position during

takeoff on one of the affected airplanes

prompted this action. The actions

specified by this AD are intended to
Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations 12409

prevent failure of the nose wheel

steering system because of a cracked

drive ring, which, if not detected and

corrected, could result in the inability to

move the rudder pedals.

DATES: Effective April 14, 1995.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of April 14,

1995.

ADDRESSES: Service information that

applies to this AD may be obtained from

Pilatus Britten-Norman Ltd, Bembridge,

Isle of Wight, United Kingdom, PO35

5PR. This information may also be

examined at the Federal Aviation

Administration (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.

Delano D. Castle, Program Manager,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

513.3830, extension 2716; facsimile

(322) 230.6899; or Mr. John P. Dow, Sr.,

Project Officer, Small Airplane

Directorate, Airplane Certification

Service, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106; telephone

(816) 426–6932; 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 Pilatus Britten-Norman BN2A,

BN2B, and BN2T Islander and BN2A

Mk III Trislander series airplanes that

are equipped with a nose wheel steering

disconnect system with either a

Modification NB/M/503 or Modification

NB/M/733 nose undercarriage unit was

published in the Federal Register on

October 25, 1994 (59 FR 53615). The

action proposed to require repetitively

inspecting the nose wheel steering drive

ring for cracks, and replacing any

cracked drive ring. The proposed

inspection would be accomplished in

accordance with Pilatus Britten-Norman

Service Bulletin No. BN–2/SB.214, Issue

1, dated September 23, 1993. The drive

ring replacement, if necessary, would be

accomplished in accordance with the

applicable maintenance manual.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

After careful review of all available

information, the FAA has determined

that air safety and the public interest

require the adoption of the rule as

proposed except for minor editorial

corrections. The FAA has determined

that these minor corrections will not

change the meaning of the AD or add

any additional burden upon the public

than was already proposed.

The FAA estimates that 15 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

1 workhour per airplane to accomplish

the required action, and that the average

labor rate is approximately $60 an hour.

Based on these figures, the total cost

impact of the AD on U.S. operators is

estimated to be $900. This figure does

not take into account the cost of

repetitive inspections or the cost of

replacing any cracked drive ring. The

FAA has no way of determining how

many repetitive inspections each

owner/operator would incur over the

life of the airplane or how many drive

rings may be cracked.

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 copy of the final

evaluation prepared for this action is

contained in the Rules Docket. A copy

of it may be obtained by contacting 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 a new AD to read as follows:

95–04–09 Pilatus Britten-Norman:

Amendment 39–9161; Docket No. 94–

CE–10–AD.

Applicability: BN2A, BN2B, and BN2T

Islander and BN2A Mk III Trislander series

airplanes, certificated in any category, that

are equipped with a nose wheel steering

disconnect system with either a Modification

NB/M/503 or Modification NB/M/733 nose

undercarriage unit.

Compliance: Required within the next 100

hours time-in-service (TIS), unless already

accomplished, and thereafter at intervals not

to exceed 100 hours TIS.

To prevent failure of the nose wheel

steering system because of a cracked drive

ring, which, if not detected and corrected,

could result in the inability to move the

rudder pedals, accomplish the following:

(a) Visually inspect the nose wheel steering

drive ring for cracks in accordance with the

ACTION section of Pilatus Britten-Norman

Service Bulletin No. BN–2/SB.214, Issue 1,

dated September 23, 1993. Prior to further

flight, replace any cracked nose wheel

steering drive ring in accordance with the

applicable maintenance manual.

(b) 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.

(c) An alternative method of compliance or

adjustment of the initial or repetitive

compliance time that provides an equivalent

level of safety may be approved by the

Manager, Brussels Aircraft Certification

Office (ACO), FAA, Europe, Africa, and

Middle East Office, c/o American Embassy,

B–1000 Brussels, Belgium. The request

should be forwarded through an appropriate

FAA Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels ACO.

Note: Information concerning the existence

of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels ACO.

(d) The inspection required by this AD

shall be done in accordance with Pilatus

Britten-Norman Service Bulletin No. BN–2/

SB.214, Issue 1, dated September 23, 1993.

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 Pilatus Britten-Norman Ltd., Bembridge,

Isle of Wight, United Kingdom, PO35 5PR.

Copies may be inspected at the FAA, Central

Region, Office of the Assistant Chief Counsel,

Room 1558, 601 E. 12th Street, Kansas City,
12410 Federal Register / Vol. 60, No. 44 / Tuesday, March 7, 1995 / Rules and Regulations

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(e) This amendment (39–9161) becomes

effective on April 14, 1995.

Issued in Kansas City, Missouri, on

February 14, 1995.

Barry D. Clements,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 95–4369 Filed 3–6–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–153–AD; Amendment

39–9160; AD 95–04–08]

Airworthiness Directives; Boeing

Model 747–300 and –400 Series

Airplanes Equipped With BFGoodrich

Stretched Upper Deck Evacuation

Slides, Part Number 7A1323–( )

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Boeing Model 747–300

and –400 series airplanes equipped with

certain stretched upper deck evacuation

slides manufactured by BFGoodrich

series airplanes. This amendment

requires modification of the slide’s main

restraint strap, regulator assembly, and

turbo fan flapper retaining roll pins.

This amendment is prompted by reports

of loss of air pressure and non-inflation

of the inflatable tubes of the slide due

to problems associated with the restraint

strap, regulator assembly, and turbo fan

flapper retaining roll pins. The actions

specified by this AD are intended to

prevent loss of air pressure or noninflation of the inflatable tubes of the

slide, which could impede the

successful evacuation of passengers

from the airplane during an emergency.

DATES: Effective 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 BFGoodrich Company, Aircraft

Evacuation Systems, Dept. 7916,

Phoenix, Arizona 85040. 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 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:

Andrew Gfrerer, Aerospace Engineer,

Systems & Equipment Branch, ANM–

130L, Los Angeles Aircraft Certification

Office, FAA, Transport Airplane

Directorate, 3960 Paramount Boulevard,

Lakewood, California 90712–4137;

telephone (310) 627–5338; fax (310)

627–5210.

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 Boeing Model 747–

300 and –400 series airplanes equipped

with BFGoodrich stretched upper deck

evacuation slides, Part Number

7A1323–( ), was published in the

Federal Register on November 30, 1994

(59 FR 61296). That action proposed to

require modification of the slide’s main

restraint strap, regulator assembly, and

turbo fan flapper retaining roll pins.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Three commenters support the

proposal.

One commenter requests that the

description of the report that prompted

the proposal be clarified. The preamble

to the notice stated that the proposed

action was based, in part, on a report

indicating that, ‘‘during deployment of

the slide, the turbo fan flapper retaining

roll pin broke, allowing the flapper to

fall out.’’ The commenter wishes to

clarify that the reported incident

occurred during the deployment of a

slide that was equipped with roll pins

that are common to those used on the

stretched upper deck escape slide;

however, there have been no reports of

roll pins breaking during deployment of

stretched upper deck slides that are the

subject of the proposed rule. The FAA

acknowledges this clarification.

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.

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 as proposed, with

the addition of the clarifying note

previously described. The FAA has

determined that the addition of the

clarifying note will neither increase the

economic burden on any operator nor

increase the scope of the AD.

There are approximately 900

BFGoodrich stretched upper deck

evacuation slides of the affected design

installed on Boeing Model 747 series

airplanes worldwide. The FAA

estimates that 100 of these slides are

installed on airplanes of U.S. registry

that are affected by this AD. It will take

approximately 4.5 work hours per slide

to accomplish the required actions, at an

average labor rate of $60 per work hour.

Required parts will cost approximately

$1,402 per slide assembly. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$167,200, or $1,672 per slide.

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.