36834 Federal Register / Vol. 63, No. 130 /Wednesday, July 8, 1998 /Rules and Regulations

Issued in Renton, Washington, on June 29,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17912 Filed 7–7–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–93–AD; Amendment

39–10644; AD 98–14–11]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A319,

A320, and A321 series airplanes, that

requires repetitive inspections for

discrepancies of the lock bolt for the

pintle pin on the main landing gear

(MLG), and follow-on corrective actions,

if necessary. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to detect and correct a rotated,

damaged, or missing lock bolt, which

could result in disengagement of the

pintle pin from the bearing, and

consequent collapse of the MLG during

landing.

DATES: Effective August 12, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 12,

1998.

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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 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 all Airbus Model

A319, A320, and A321 series airplanes

was published in the Federal Register

on May 12, 1998 (63 FR 26111). That

action proposed to require repetitive

inspections for discrepancies of the lock

bolt for the pintle pin on the main

landing gear (MLG), and follow-on

corrective actions, if necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

The commenters support the

proposed rule.

Explanation of Changes Made to This

Final Rule

In the proposal, the FAA

inadvertently omitted reference to

Revision 1, dated June 13, 1994, of

Airbus Service Bulletin A320–32–1119.

Therefore, the FAA has revised the final

rule accordingly.

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 with the change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator or increase the scope of the AD.

Interim Action

This is considered to be interim

action until final action is identified, at

which time the FAA may consider

further rulemaking.

Cost Impact

The FAA estimates that 120 airplanes

of U.S. registry will be affected by this

AD. It will take approximately 1 work

hour per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $7,200, or

$60 per airplane, per inspection cycle.

The 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.

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 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:

98–14–11 Airbus Industrie: Amendment

39–10644. Docket 98–NM–93–AD.

Applicability: All Model A319, A320, and

A321 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 request approval for an

alternative method of compliance in
Federal Register / Vol. 63, No. 130 /Wednesday, July 8, 1998 /Rules and Regulations 36835

accordance with paragraph (b) 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 detect and correct a rotated, damaged,

or missing lock bolt, which could result in

disengagement of the pintle pin from the

bearing, and consequent collapse of the main

landing gear (MLG) during landing,

accomplish the following:

(a) Perform a detailed visual inspection to

detect discrepancies (rotation, damage, and

absence) of the lock bolt for the pintle pin on

the MLG, in accordance with Airbus All

Operator Telex (AOT) 32–17, Revision 01,

dated November 6, 1997, at the latest of the

times specified in paragraphs (a)(1), (a)(2),

and (a)(3), of this AD. If any discrepancy is

detected, prior to further flight, perform

corrective actions, as applicable, in

accordance with the AOT. Repeat the

inspection thereafter at intervals not to

exceed 1,000 flight cycles or 15 months,

whichever occurs first.

(1) Within 30 months since the airplane’s

date of manufacture or prior to the

accumulation of 2,000 total flight cycles,

whichever occurs first.

(2) Within 15 months or 1,000 flight cycles

after the last gear replacement or

accomplishment of Airbus Service Bulletin

A320–32–1119, Revision 1, dated June 13,

1994, whichever occurs first.

(3) Within 500 flight cycles after the

effective date of 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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their request through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 actions shall be done in accordance

with Airbus All Operator Telex (AOT) 32–17,

Revision 01, dated November 6, 1997. 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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–385–

112(B), dated December 17, 1997.

(e) This amendment becomes effective

on August 12, 1998.

Issued in Renton, Washington, on June 29,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17911 Filed 7–7–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–95–AD; Amendment

39–10448; AD 98–07–26]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 767 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This document corrects two

typographical errors that appeared in

airworthiness directive (AD) 98–07–26,

which was published in the Federal

Register on April 6, 1998 (63 FR 16681).

The typographical errors resulted in a

reference to an incorrect part number

and incorrect section of the referenced

service information. This AD is

applicable to certain Boeing Model 767

series airplanes. This AD requires

detailed visual inspection(s) for damage

or chafing of certain electrical wire

bundles and for clearance between the

wire bundles and adjacent forward

galley air chiller; and follow-on

corrective actions.

DATES: Effective April 21, 1998.

The incorporation by reference of

certain publications listed in the

regulations was previously approved by

the Director of the Federal Register as of

April 21, 1998 (63 FR 16681, April 6,

1998).

FOR FURTHER INFORMATION CONTACT:

Elias Natsiopoulos, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–1279; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION:

Airworthiness Directive (AD) 98–07–26,

amendment 39–10448, applicable to

certain Boeing Model 767 series

airplanes, was published in the Federal

Register on April 6, 1998 (63 FR 16681).

That AD requires detailed visual

inspection(s) for damage or chafing of

certain electrical wire bundles and for

clearance between the wire bundles and

adjacent forward galley air chiller; and

follow-on corrective actions.

As published, that AD contained two

typographical errors in paragraphs

(a)(1)(ii), (a)(2), (a)(3)(ii), and (a)(4).

First, those paragraphs identified

‘‘Section 20–00–11’’ of the Boeing

Standard Wiring Practices Manual as

the appropriate source of service

information for accomplishment of the

actions. However, the correct section

should have been identified as ‘‘Section

20–10–11.’’ Second, those paragraphs

identified ‘‘TFX–2X standard wall

thickness (sleeve)’’ as one of the

appropriate materials to protect the

bundles. However, part number (P/N)

‘‘TFX–2X’’ was indicated inadvertently

in those paragraphs instead of the

correct P/N ‘‘TFE–2X.’’ (In fact, P/N

‘‘TFX–2X’’ does not exist.)

Since no other part of the regulatory

information has been changed, the final

rule is not being republished.

The effective date of this AD remains

April 21, 1998.

In final rule, FR Doc. 98–8705,

published on April 6, 1998 (63 FR

16681), make the following corrections:

§ 39.13 [Corrected]

1. On page 16683, in the first column,

paragraph (a)(1)(ii) of AD 98–07–26 is

corrected to read as follows:

* * * * *

(a) * * *

(1) * * *

(ii) Prior to further flight, install

protective tape or sleeve over the wire

bundles, in accordance with Section 20–

10–11 of the Boeing Standard Wiring

Practices Manual. Operators shall use

one of the following materials to protect

the bundles: RT876 (sleeve), TFE–2X

standard wall thickness (sleeve), P–440

(tape), Scotch 70 (tape), or CHR–A–2005

(tape).

* * * * *

2. On page 16683, in the first column,

paragraph (a)(2) of AD 98–07–26 is

corrected to read as follows:

* * * * *

(a) * * *

(2) If no damage or chafing is detected

and inadequate clearance exists, prior to

further flight, modify the routing of the

wire bundles in accordance with the

Boeing message, and install protective

tape or sleeve over the wire bundles in

accordance with Section 20–10–11 of

the Boeing Standard Wiring Practices

Manual. Operators shall use one of the

following materials to protect the

bundles: RT876 (sleeve), TFE–2X