Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations 34059

Incorporation by Reference

(o) Except as required by paragraphs (a)(2), (a)(2)(ii), (a)(3), (b)(2), (c)(2), (c)(2)(ii), (c)(3), (d)(2), (e)(2), (e)(2)(ii), (e)(3), (f)(2), (g)(2),

(g)(2)(ii), (g)(3), (h)(2), (k)(1)(ii), (k)(2), and (l)(2), the actions shall be done in accordance with the following Airbus service bulletins:

Airbus service bulletin No. Revision level Service bulletin

date

A300–54–0073, ....................................................................................................................................... 1 ............................. March 28, 1994.

A300–54–6014, ....................................................................................................................................... 1 ............................. March 28, 1994.

A310–54–2017, ....................................................................................................................................... 03 ........................... June 11, 1999.

A310–54–2023, ....................................................................................................................................... Original .................. October 15, 1993.

(1) The incorporation by reference of

Airbus Service Bulletin A310–54–2017,

Revision 03, dated June 11, 1999, is

approved by the Director of the Federal

Register, in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51.

(2) The incorporation by reference of the

remaining service bulletins was approved

previously by the Director of the Federal

Register as of June 28, 1996 (61 FR 26091,

May 24, 1996).

(3) 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 directives 1999–

239–287(B) and 1993–228–154(B)R3, both

dated June 2, 1999.

(p) This amendment becomes effective on

June 30, 2000.

Issued in Renton, Washington, on May 16,

2000.

Donald L. Riggin,

Acting Manager,Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–12814 Filed 5–25–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–28–AD; Amendment

39–11740; AD 2000–10–16]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A319, A320, and A321 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A319, A320, and A321 series airplanes,

that currently 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 requires additional followon actions for certain airplanes. This

amendment also provides for optional

terminating action for the requirements

of this AD. 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 pintle fitting

bearing, and consequent collapse of the

MLG during landing.

DATES: Effective June 30, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 30,

2000.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of August 12, 1998 (63 FR

36834, July 8, 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)

by superseding AD 98–14–11,

amendment 39–10644 (63 FR 36834,

July 8, 1998), which is applicable to all

Airbus Model A319, A320, and A321

series airplanes, was published in the

Federal Register on February 24, 2000

(65 FR 9225). The action proposed to

continue 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; and to

require additional follow-on actions,

including a retorque of the lock bolt for

the pintle pin.

Comment Received

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

Reference to Terminating Modification

Two commenters request that the

proposed AD include reference to

Airbus Modifications 28903 (for Model

A319 and A320 series airplanes) and

30044 (for Model A321 series airplanes)

as terminating action to the

requirements of this AD. Airbus Service

Bulletin A320–32–1213, dated March

21, 2000, describes procedures for

accomplishment of the modification,

which involves installation of a dual

lock bolt configuration. One commenter

notes that the Direction Ge ́ne ́rale de

l’Aviation Civile (DGAC), which is the

airworthiness authority of France, has

approved this modification as

terminating action for the inspections

and actions described in Airbus Service

Bulletin A320–32–1187.

The FAA concurs that the

modification described in Airbus

Service Bulletin A320–32–1213

constitutes acceptable terminating

action to the requirements of this AD. A

new paragraph (c) has been added to the

AD to provide this option to operators,

and the applicability of the AD has been

limited to those airplanes not having the

modification. Additionally, since

terminating action is now available, the

FAA has removed the ‘‘Interim Action’’

discussion from the AD; however, the

FAA may consider further rulemaking if

34060 Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations

a determination is made at a later date

that the terminating modification

should be mandated.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

previously described. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

There are approximately 341

airplanes of U.S. registry that will be

affected by this AD. It will take

approximately 2 work hours 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 $40,920, or $120 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 a substantial direct effect 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, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

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

removing amendment 39–10644 (63 FR

36834, July 8, 1998), and by adding a

new airworthiness directive (AD),

amendment 39–11740, to read as

follows:

2000–10–16 Airbus Industrie: Amendment

39–11740. Docket 99–NM–28–AD.

Supersedes AD 98–14–11, Amendment

39–10644.

Applicability: Model A319, A320, and

A321 series airplanes, certificated in any

category, except those on which Airbus

Service Bulletin A320–32–1213, dated March

21, 2000 (reference Airbus Modification

28903 or 30044), has been accomplished.

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 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:

Inspection

(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, Airbus Service

Bulletin A320–32–1187, dated June 17, 1998,

or Airbus Service Bulletin A320–32–1187,

Revision 01, dated February 17, 1999, 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 or

service bulletin. Repeat the inspection

thereafter at intervals not to exceed 1,000

flight cycles or 15 months, whichever occurs

first, unless the terminating action of

paragraph (c) of this AD is accomplished.

After the effective date of this AD, only

Airbus Service Bulletin A320–32–1187,

Revision 01, dated February 17, 1999, shall

be used for compliance with this paragraph.

(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 Industrie Service

Bulletin A320–32–1119, dated June 13, 1994,

whichever occurs first.

(3) Within 500 flight cycles after August

12, 1998 (the effective date of AD 98–14–11,

amendment 39–10644).

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

One-Time Follow-On Actions

(b) For airplanes on which the actions

described in paragraph 2.B.(2)(c) of Airbus

Service Bulletin A320–32–1187, Revision 01,

dated February 17, 1999, have not been

accomplished: At the time of the initial

inspection or the next repetitive inspection

required by paragraph (a) of this AD, perform

the applicable one-time follow-on actions

(including retorquing the forward pintle pin

lock bolt and applying sealant to the head of

the lock bolt), in accordance with section

2.B.(2)(c) of the Accomplishment Instructions

of Airbus Service Bulletin A320–32–1187,

Revision 01, dated February 17, 1999.

Optional Terminating Modification

(c) Modification of the lock bolts of the bolt

for the pintle pin on the MLG in accordance

with Airbus Service Bulletin A320–32–1213,

dated March 21, 2000, constitutes

terminating action for the requirements of

this AD.

Alternative Methods of Compliance

(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,

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Federal Register / Vol. 65, No. 103 / Friday, May 26, 2000 / Rules and Regulations 34061

Special Flight Permits

(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.

Incorporation by Reference

(f) The actions shall be done in accordance

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

Revision 01, dated November 6, 1997; Airbus

Service Bulletin A320–32–1187, dated June

17, 1998; or Airbus Service Bulletin A320–

32–1187, Revision 01, dated February 17,

1999.

(1) The incorporation by reference of

Airbus Service Bulletin A320–32–1187,

dated June 17, 1998, and Airbus Service

Bulletin A320–32–1187, Revision 01, dated

February 17, 1999, is approved by the

Director of the Federal Register in accordance

with 5 U.S.C. 552(a) and 1 CFR part 51.

(2) The incorporation by reference of

Airbus All Operator Telex (AOT) 32–17,

Revision 01, dated November 6, 1997, was

approved previously by the Director of the

Federal Register as of August 12, 1998 (63 FR

36834, July 8, 1998).

(3) 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 4: The subject of this AD is addressed

in French airworthiness directive 97–385–

112(B)R1, dated October 21, 1998.

(g) This amendment becomes effective on

June 30, 2000.

Issued in Renton, Washington, on May 16,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–12815 Filed 5–25–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–88–AD; Amendment

39–11748; AD 2000–10–23]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, –200, –300, 747SR, and

747SP Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747–

100, –200, –300, 747SR, and 747SP

series airplanes, that currently requires

a one-time inspection to detect cracking

of the longeron splice fittings at stringer

11, on the left and right sides at body

station 2598, and replacement of any

cracked fitting with a new fitting. This

amendment reduces the compliance

time for accomplishment of the

currently required inspection and adds

a new requirement for repetitive

inspections. This amendment is

prompted by reports that fatigue

cracking was found on longeron splice

fittings. The actions specified by this

AD are intended to detect and correct

such fatigue cracking, which could

result in reduced controllability of the

horizontal stabilizer.

DATES: Effective June 30, 2000.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

53A2410, Revision 2, including

Addendum, dated October 30, 1997, as

listed in the regulations, is approved by

the Director of the Federal Register as of

June 30, 2000.

The incorporation by reference of

Boeing Service Bulletin 747–53A2410,

Revision 3, including Addendum, dated

March 12, 1998, as listed in the

regulations, was approved previously by

the Director of the Federal Register as of

January 13, 1998 (62 FR 67550,

December 29 1997).

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Airplane

Group, P.O. Box 3707, Seattle,

Washington 98124–2207. 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: Rick

Kawaguchi, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–1153;

fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 97–26–21,

amendment 39–10264 (62 FR 67550,

December 29 1997), which is applicable

to certain Boeing Model 747–100, –200,

–300, 747SR, and 747SP series

airplanes, was published in the Federal

Register on February 22, 2000 (65 FR

8667). The action proposed to continue

to require a one-time inspection to

detect cracking of the longeron splice

fittings at stringer 11, on the left and

right sides at body station 2598, and

replacement of any cracked fitting with

a new fitting. The action also proposed

to reduce the compliance time for

accomplishment of the currently

required inspection and add a new

requirement for repetitive inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 685

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

99 airplanes of U.S. registry will be

affected by this AD.

The inspection that is currently

required by AD 97–26–21 takes

approximately 32 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour.

Based on these figures, the cost

impact of the currently required actions

on U.S. operators is estimated to be

$190,080, or $1,920 per airplane.

This AD requires the same inspection

currently required by AD 97–26–21 to

be accomplished repetitively. Therefore,

the cost impact of the requirements of

this AD on U.S. operators is estimated

to be $190,080, or $1,920 per airplane,

per inspection cycle.

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 a substantial direct effect 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, it is determined that this

final rule does not have federalism

implications under Executive Order

13132.

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