14794 Federal Register / Vol. 62, No. 60 / Friday, March 28, 1997 / Rules and Regulations

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. 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

97–07–02 Airbus Industrie: Amendment 39–

9975. Docket 96–NM–107–AD.

Applicability: Model A300 airplanes

having serial numbers 001 through 0156,

inclusive, certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent fatigue cracking of the rear

pressure bulkhead, which could reduce its

structural integrity, and consequently lead to

rapid depressurization of the airplane,

accomplish the following:

(a) Within 12 months after the effective

date of this AD, perform a template

inspection to detect dents of the rear pressure

bulkhead in the area between right hand and

left hand radial stiffeners RS 5 and RS 13, in

accordance with Airbus Service Bulletin

A300–53–302, dated November 3, 1995.

(b) If no dent, or if no dent that is greater

than 2 mm in depth, is detected during the

template inspection required by paragraph (a)

of this AD: No further action is required by

this AD.

(c) If any dent that is greater than 2 mm

in depth is detected during the template

inspection required by paragraph (a) of this

AD: Prior to further flight, inspect the dent

for cracking, in accordance with Airbus

Service Bulletin A300–53–302, dated

November 3, 1995.

(1) If no crack is detected: Repeat the

inspection for cracking at intervals not to

exceed 2,000 landings until the permanent

repair specified in paragraph (c)(1)(i) of this

AD is accomplished.

(i) Prior to the accumulation of 5 years or

11,000 landings after the effective date of this

AD, whichever occurs first, accomplish the

permanent repair of the dent in accordance

with paragraph 2.B.(3)(c)1 of the

Accomplishment Instructions of the service

bulletin.

(ii) Accomplishment of the permanent

repair of the dent constitutes terminating

action for the repetitive inspection

requirements of this paragraph, and

thereafter, no further action is required.

(2) If only radial cracking is detected in the

circumferential strap and no other cracking is

found elsewhere in the rear pressure

bulkhead: Prior to further flight, accomplish

the circumferential strap repair, in

accordance with paragraph 2.B.(3)(c)2 of the

Accomplishment Instructions of the service

bulletin. Thereafter, inspect the dent for

cracking at intervals not to exceed every

1,000 landings until the permanent repair

specified in paragraph (c)(2)(i) of this AD is

accomplished.

(i) Prior to the accumulation of 5 years or

11,000 landings after the effective date of this

AD, whichever occurs first, accomplish

permanent repair of the dent in accordance

with the paragraph 2.B.(3)(c)2 of the

Accomplishment Instructions of the service

bulletin.

(ii) Accomplishment of the permanent

repair of the dent constitutes terminating

action for the repetitive inspection and repair

requirements of this paragraph and

thereafter, no further action is required.

(3) If any other cracking not specified in

paragraph (c)(1) or (c)(2) of this AD is

detected: Prior to further flight, accomplish a

permanent repair of the dent in accordance

with the paragraph 2.B.(3)(c) 3 or 4, as

applicable, of the Accomplishment

Instructions of the service bulletin; or in a

manner approved by the Manager,

Standardization Branch, ANM–113, FAA,

Transport Airplane Directorate.

Accomplishment of the permanent repair of

the dent in accordance with the

Accomplishment Instructions of the service

bulletin constitutes terminating action for the

requirements of this AD and, thereafter, no

further action is required.

(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 shall be done in accordance

with Airbus Service Bulletin A300–53–302,

dated November 3, 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 Airbus Industrie, 1 Rond

Point Maurice Bellonte, 31707 Blagnac

Cedex, France. 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 2, 1997.

Issued in Renton, Washington, on March

19, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–7517 Filed 3–27–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–29–AD; Amendment 39–

9976; AD 97–07–03]

RIN 2120–AA64

Airworthiness Directives; The New

Piper Aircraft, Inc. Models PA31,

PA31–300, PA31–325, PA31–350, and

PA31P Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 81–11–04

that applies to The New Piper Aircraft,

Inc. (Piper) Models PA31, PA31–300,

PA31–325, and PA31–350 airplanes that

have Cleveland nose wheel assembly

part number (P/N) 40–76B installed. AD

81–11–04 currently requires inspecting

the nose wheel flange for cracks. The

repetitive inspections terminate by

replacing the nose wheel assembly with
Federal Register / Vol. 62, No. 60 / Friday, March 28, 1997 / Rules and Regulations 14795

Cleveland P/N 40–140, which is an

improved design. This action is

prompted by the lack of designation of

Piper Model PA31P in the Applicability

section of AD 81–11–04, and the

subsequent failure of a nose wheel

assembly on a Piper Model PA31P

airplane during taxiing operations. The

actions specified by this AD are

intended to prevent the failure of the

nose wheel, which if not corrected,

could result in loss of control of the

airplane during taxiing, take-off, or

landing operations.

DATES: Effective May 15, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 15,

1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

The New Piper Aircraft, Inc., Attn:

Customer Service, 2926 Piper Dr., Vero

Beach, Florida, 32960. This information

may also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket 96–

CE–29–AD, 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:

Christina Marsh, Aerospace Engineer,

FAA, Atlanta Aircraft Certification

Office, Campus Building, 1701

Columbia Ave., suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7362, facsimile (404) 305–

7348.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to PA31, PA31–325, PA31–350,

and PA31P airplanes that have

Cleveland nose wheel assembly part

number (P/N) 40–76B installed was

published in the Federal Register on

October 10, 1996 (61 FR 53155). This

action would supersede AD 81–11–04

with a new AD that retains the same

action as AD 81–11–04 and include

Piper Model PA31P airplanes in the

applicability. Accomplishment of the

proposed action would be in accordance

with Piper Service Bulletin (SB) 700A,

dated October 12, 1981.

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.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. One minor

editorial correction is a missing model

number that is affected by this AD. The

FAA inadvertently omitted Model

PA31–300 from the applicability listing

in the NPRM, however the PA31–300

serial numbers were listed. Piper

manufactured Models PA31, PA31–300,

and PA31–325 airplanes

simultaneously, so the serial number

range listed for Models PA31 and PA31–

325 airplanes in the NPRM applicability

section also included the Model PA31–

300 airplanes. The applicability section

now contains Model PA31–300 with the

appropriate serial numbers. The FAA

has determined that these minor

corrections will not change the meaning

of the AD and will not add any

additional burden upon the public than

was already proposed.

Cost Impact

The FAA estimates that 1,842

airplanes in the U.S. registry will be

affected by this AD, that it will take

approximately 3 workhours per airplane

to accomplish this action, and that the

average labor rate is approximately $60

an hour. The improved parts cost

approximately $450 per airplane. Based

on these figures, the total cost impact of

this AD on U.S. operators is estimated

to be $1,160,460 or $630 per airplane.

These figures only account for the

replacement of the new part and do not

take into account the cost for the

repetitive inspections that would be

incurred prior to installing the

improved parts.

Piper has informed the FAA that parts

have been distributed to equip 8

airplanes in the United States which

will reduce the total figure from

$1,160,460 to $1,155,420.

Regulatory Impact

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 USC 106(g), 40113, 44701.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

97–07–03 The New Piper Aircraft, Inc.:

Amendment 39–9976; Docket No. 96–

CE–29–AD, Supersedes AD 81–11–04,

Amendment 39–4114.

Applicability: The following Models and

serial numbered airplanes equipped with

Cleveland part number (P/N) 40–76B (Piper

P/N 451 784) nose wheel assembly,

certificated in any category.

Models Serial numbers

PA31, PA31–300, and

PA31–325.

31–2 through 31–

8112038

PA31–350 .................. 31–5001 through 31–

8152088

PA31P ....................... 31P–3 through 31P–

7730012

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 request approval for an

alternative method of compliance in

accordance with paragraph (d) of this AD.
14796 Federal Register / Vol. 62, No. 60 / Friday, March 28, 1997 / Rules and Regulations

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required within the next 100

hours time-in-service (TIS) after May 22,

1981 (effective date of AD 81–11–04); within

the next 100 hours TIS after the effective date

of this AD; or upon the accumulation of

2,000 hours TIS on the nose wheel assembly,

whichever occurs later, unless already

accomplished.

To prevent the failure of the nose wheel,

which if not corrected, could result in loss

of control of the airplane during taxiing, takeoff, or landing operations, accomplish the

following:

(a) Inspect the nose wheel assembly,

Cleveland part number (P/N) 40–76B (The

New Piper Aircraft, Inc. P/N 451 784), for

cracks in accordance with the ‘‘Instructions’’

section of Piper Aircraft Corporation (Piper)

Service Bulletin (SB) 700A, dated October 12,

1981.

(1) If cracked, prior to further flight,

replace Cleveland P/N 40–76B (Piper P/N

451 784) with a new Cleveland P/N 40–76B

(Piper P/N 451 784) nose wheel assembly.

Upon the accumulation of 2,000 hours TIS,

reinspect at 100 hour intervals or at each tire

change, whichever occurs first; or,

(2) As an alternative to paragraph (a)(1), if

cracked, replace Cleveland P/N 40–76B

(Piper P/N 451 784) with a serviceable

Cleveland P/N 40–140 (Piper P/N 551 791)

nose wheel assembly of improved design in

accordance with the ‘‘Instructions’’ section of

Piper SB 700A, dated October 12, 1981.

(3) If no cracks are found and Cleveland P/

N 40–140 (Piper P/N 551–791) is not

installed, repetitively inspect at intervals not

to exceed 100 hours TIS or at each tire

change, whichever occurs first.

(b) The installation of Cleveland P/N 40–

140 (Piper P/N 551 791) is considered

terminating action for the inspection

requirements of paragraph (a) and (a)(3) of

this AD.

(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) An alternative method of compliance or

adjustment of the compliance times that

provides an equivalent level of safety may be

approved by the Manager, FAA, Atlanta

Aircraft Certification Office, Campus

Building, 1701 Columbia Ave., suite 2–160,

College Park, Georgia 30337–2748. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Atlanta Aircraft Certification

Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from Atlanta Aircraft Certification

Office.

(e) The inspections and replacement

required by this AD shall be done in

accordance with Piper Aircraft Corporation

Service Bulletin No. 700A, dated October 12,

1981. 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 The New Piper Aircraft, Inc., Attn.:

Customer Service, 2926 Piper Dr., Vero

Beach, Florida, 32960. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(f) This amendment (39–9976) becomes

effective on May 15, 1997.

Issued in Kansas City, Missouri, on March

20, 1997.

Larry E. Werth,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–7680 Filed 3–27–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 71

[Airspace Docket No. 96–AAL–27]

Revision of Class E Airspace; Nuiqsut,

AK

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final Rule.

SUMMARY: This action revises Class E

airspace at Nuiqsut Airport, AK. The

modifications to the Global Positioning

System (GPS) instrument approaches to

runway (RWY) 4 and RWY 22 at

Nuiqsut, AK, have made this action

necessary. The intended effect of this

action is to provide adequate controlled

airspace for Instrument Flight Rules

(IFR) operations at Nuiqsut Airport, AK.

EFFECTIVE DATE: 0901 UTC, May 22,

1997.

FOR FURTHER INFORMATION CONTACT:

Robert van Haastert, System

Management Branch, AAL–538, Federal

Aviation Administration, 222 West 7th

Avenue, Box 14, Anchorage, AK 99513–

7587; telephone number: (907) 271–

5863; email:

Robert.van.Haastert@faa.dot.gov.

SUPPLEMENTARY INFORMATION:

History

On January 24, 1997, a proposal to

amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) to revise

the Class E airspace at Nuiqsut was

published in the Federal Register (62

FR 3631). The modifications to the GPS

instrument approach procedures to

RWY 4 and RWY 22 at Nuiqsut Airport,

AK, have made this action necessary.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments to the proposal were

received, thus the rule is adopted as

written.

The coordinates for this airspace

docket are based on North American

Datum 83. The Class E airspace areas

designated as 700/1200 foot transition

areas are published in paragraph 6005 of

FAA Order 7400.9D, Airspace

Designations and Reporting Points,

dated September 4, 1996, and effective

September 16, 1996. Paragraph 6005 is

incorporated by reference in 14 CFR

71.1 (61 FR 48403; September 13, 1996).

The Class E airspace designations listed

in this document will be published

subsequently in the Order.

The Rule

This amendment to part 71 of the

Federal Aviation Regulations (14 CFR

part 71) revises Class E airspace located

at Nuiqsut, AK, to provide controlled

airspace extending upward from 700

feet AGL for aircraft executing

instrument landing and departing

procedures.

The Federal Aviation Administration

has determined that these proposed

regulations only involve an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore—(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)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR Part 71

Airspace, Incorporation by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR part 71 as follows:

PART 71—[AMENDED]

1. The authority citation for 14 CFR

Part 71 continues to read as follows:

Authority: 49 U.S.C. 40103, 40113, 40120;

E.O. 10854, 24 FR 9565, 3 CFR, 1959–1963

Comp., p. 389; 49 U.S.C. 106(g); 14 CFR

11.69.