Federal Register / Vol. 62, No. 60 / Friday, March 28, 1997 / Rules and Regulations 14793

(4) Extension of time period for final

Board action. To extend for an

additional 180 days the 180-day period

within which final Board action is

required on an application pursuant to

section 7(d) of the International Banking

Act.

* * * * *

By order of the Board of Governors of the

Federal Reserve System, March 24, 1997.

William W. Wiles,

Secretary of the Board.

[FR Doc. 97–7910 Filed 3–27–97; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–107–AD; Amendment

39–9975; AD 97–07–02]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Airbus Model

A300 series airplanes. It requires a onetime template inspection of the rear

pressure bulkhead to detect dents;

repetitive eddy current inspections of

dents greater than a certain depth to

detect cracking; and repair, if necessary.

This amendment is prompted by a

report indicating that cracking has been

found in the vicinity of a dent in the

rear pressure bulkhead of one airplane.

The actions specified by this

amendment are intended to prevent

fatigue cracking resulting from a dent in

the rear pressure bulkhead; that

condition, if not corrected, could reduce

the structural integrity of the bulkhead

and, consequently, lead to rapid

depressurization of the airplane.

DATES: Effective May 2, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 2,

1997.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. 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: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

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 Airbus

Model A300 series airplanes was

published in the Federal Register on

November 5, 1996 (61 FR 56923). That

action proposed to require a one-time

template inspection of the rear pressure

bulkhead to detect dents; repetitive

eddy current inspections of dented areas

greater than a certain depth to detect

fatigue cracking; and repair, if

necessary.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Support for the Proposal

One commenter supports the

proposed AD.

Request to Explain Adequacy of OneTime Inspection

One commenter asks if a one-time

inspection, as would be required by the

AD, is adequate to address the subject

fatigue cracking. The commenter points

out that if the inspection finds no dents

of a depth greater than 2 mm, no further

action would be required; consequently,

any subsequent detection of dents/

cracking will depend upon the existing

level and frequency of inspections in

the operators’ existing maintenance

program, specifically the Maintenance

Planning Document (MPD). The

commenter questions whether the

inspections scheduled under the current

MPD are adequate to ensure that any

small dents are subsequently found and

corrected in a timely manner.

The FAA responds to this comment

by reiterating the circumstances relevant

to the cracking addressed by this AD

action. The subject cracks were detected

on the rear pressure bulkhead on one

airplane during a heavy maintenance

check. The cracks were found to initiate

from a dent in the bulkhead. Airbus

conducted analyses and calculations of

the dent and associated cracking, which

demonstrated that:

1. The force necessary to make a dent

of this sort in the rear pressure bulkhead

in the specific location could not have

been generated in service, and

2. The dent was unique to the

production process.

The purpose of the one-time

inspection required by this AD is to

detect dents as small as 2mm in depth

in the rear pressure bulkhead that may

have occurred during production. To

accomplish this, the inspection makes

use of a template in accordance with

Airbus Service Bulletin A300–53–302,

because the inspections conducted

under the MPD cannot detect small

dents of this type. The inspections that

are part of the MPD are visual

inspections, and are considered

adequate to detect defects of the rear

pressure bulkhead that may occur in

service.

Conclusion

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.

Cost Impact

The FAA estimates that 15 Airbus

Model A300 series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 5 work hours

per airplane to accomplish the required

inspection for denting, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $4,500, or $300 per airplane.

If subsequent eddy current

inspections to detect cracking are

necessary, they would require 46 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of these inspections on U.S. operators is

estimated to be $2,760 per airplane per

inspection.

The cost impact figures discussed

above are 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.

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.
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