Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations 39077

accordance with paragraph (g) 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 cracking in the aft

pressure bulkhead, which could result in

rapid decompression of the fuselage or

overpressurization of the tail section,

accomplish the following:

Initial and Repetitive Inspections

(a) Except as provided by paragraph (f) of

this AD, prior to the accumulation of 20,000

total flight cycles, or within 12 months after

the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection of the upper half of the aft

pressure bulkhead to detect cracking, in

accordance with Figure 6 or 7, as applicable,

of Boeing Alert Service Bulletin 747–

53A2425, dated October 29, 1998. Repeat the

detailed visual inspection thereafter at

intervals not to exceed 1,500 flight cycles.

For areas of the upper half of the aft pressure

bulkhead that have been repaired previously,

this detailed visual inspection may be

deferred for up to 15,000 flight cycles after

accomplishment of the repair, as described in

the NOTE in paragraph 3.D. of the

Accomplishment Instructions of the alert

service bulletin.

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.’’

(b) Except as provided by paragraph (f) of

this AD, if no cracking is detected during the

initial detailed visual inspection required by

paragraph (a) of this AD: Within 1,500 flight

cycles after accomplishment of that

inspection, perform a high frequency eddy

current (HFEC) inspection of the upper and

lower halves of the aft pressure bulkhead to

detect cracking, in accordance with Figure 8

of Boeing Alert Service Bulletin 747–

53A2425, dated October 29, 1998. Repeat the

HFEC inspection thereafter at intervals not to

exceed 3,000 flight cycles.

(c) Except as provided by paragraph (f) of

this AD, if any cracking is detected during

any inspection required by paragraph (a) of

this AD: Prior to further flight, perform an

HFEC inspection of the upper and lower

halves of the aft pressure bulkhead to detect

cracking, in accordance with Figure 8 or 9,

as applicable, of Boeing Alert Service

Bulletin 747–53A2425, dated October 29,

1998. Repeat the HFEC inspection thereafter

at intervals not to exceed 3,000 flight cycles.

Repair

(d) Except as provided by paragraphs (e)

and (f) of this AD, if any cracking is detected

during any inspection required by paragraph

(a), (b), or (c) of this AD: Prior to further

flight, repair in accordance with Boeing Alert

Service Bulletin 747–53A2425, dated October

29, 1998.

(e) If any cracking is detected during any

inspection required by paragraph (a), (b), or

(c) of this AD, and Boeing Alert Service

Bulletin 747–53A2425, dated October 29,

1998, specifies to contact Boeing for repair

instructions: Repair any cracking, prior to

further flight, in accordance with a method

approved by the Manager, Seattle Aircraft

Certification Office (ACO), FAA, Transport

Airplane Directorate; or in accordance with

data meeting the type certification basis of

the airplane approved by a Boeing Company

Designated Engineering Representative (DER)

who has been authorized by the Manager,

Seattle ACO, to make such findings. For a

repair method to be approved by the

Manager, Seattle ACO, as required by this

paragraph, the approval letter must

specifically reference this AD.

Operator’s ‘‘Equivalent Procedure’’

(f) Where Boeing Alert Service Bulletin

747–53A2425, dated October 29, 1998,

specifies that an inspection or a repair, as

applicable, may be accomplished in

accordance with an operator’s ‘‘equivalent

procedure’’: The inspection or repair, as

applicable, must be accomplished in

accordance with the applicable chapter of the

Boeing 747 Maintenance Manual or the

Boeing 747 Structural Repair Manual

specified in the alert service bulletin.

Alternative Methods of Compliance

(g) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(h) 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

(i) Except as provided by paragraphs (e)

and (f) of this AD, the actions shall be done

in accordance with Boeing Alert Service

Bulletin 747–53A2425, dated October 29,

1998. 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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

(j) This amendment becomes effective on

July 28, 2000.

Issued in Renton, Washington, on June 12,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15308 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–77–AD; Amendment

39–11798; AD 2000–12–20]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 series airplanes, that requires

modification of the position 1 flap screw

jack. 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 prevent fracture of the lead

screw of the position 1 flap screw jack,

which could result in failure of the tie

bar and possible disconnection of the

flap structure from the airplane.

DATES: Effective July 28, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 28,

2000.

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,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

39078 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

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 certain Airbus

Model A310 series airplanes was

published in the Federal Register on

April 19, 2000 (65 FR 20921). That

action proposed to require modification

of the position 1 flap screw jack.

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

The FAA estimates that 41 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required modification, and that the

average labor rate is $60 per work hour.

Required parts will cost approximately

$105 per airplane. Based on these

figures, the cost impact of the required

modification AD on U.S. operators is

estimated to be $9,225, or $225 per

airplane.

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

adding the following new airworthiness

directive:

2000–12–20 Airbus Industrie: Amendment

39–11798. Docket 2000–NM–77–AD.

Applicability: Model A310 series airplanes,

certificated in any category, except those

airplanes on which Airbus Modification

10855 or Airbus Service Bulletin A310–27–

2075 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 (c) 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 fracture of the lead screw of the

position 1 flap screw jack, which could result

in failure of the tie bar and possible

disconnection of the flap structure from the

airplane, accomplish the following:

Modification

(a) Within 18 months after the effective

date of this AD, modify the position 1 flap

screw jack in accordance with Airbus Service

Bulletin A310–27–2075, Revision 02, dated

February 8, 2000.

Note 2: Modifications accomplished prior

to the effective date of this AD, in accordance

with Airbus Service Bulletin A310–27–2075,

dated November 18, 1994, or Revision 01,

dated July 20, 1995, are considered

acceptable for compliance with the

modification specified by this AD.

Note 3: The Airbus service bulletin

references Lucas/Liebherr Service Bulletin

537–27-M537–15, dated May 12, 1994, as an

additional source of service information for

accomplishing the applicable action required

by this AD.

Spares

(b) As of the effective date of this AD, no

person shall install on any airplane a

position 1 flap screw jack having part

number 537G0000–02, unless modified in

accordance with this AD.

Alternative Methods of Compliance

(c) 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 requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(d) 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

(e) The modification shall be done in

accordance with Airbus Service Bulletin

A310–27–2075, Revision 02, dated February

8, 2000. 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 5: The subject of this AD is addressed

in French airworthiness directive 1999–510–

299(B), dated December 29, 1999.

(f) This amendment becomes effective on

July 28, 2000.

Issued in Renton, Washington, on June 12,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15307 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–P