This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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Rules and Regulations Federal Register

33459

Vol. 66, No. 121

Friday, June 22, 2001

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–354–AD; Amendment

39–12279; AD 2001–12–23]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, 747–200, 747–300,

747SP, and 747SR Series Airplanes

Powered by Pratt & Whitney JT9D–3

and JT9D–7 Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Boeing Model 747–

100, 747–200, 747–300, 747SP, and

747SR series airplanes powered by Pratt

& Whitney JT9D–3 or JT9D–7 series

engines, that currently requires

inspections of the vertical chords of the

aft torque bulkhead of the outboard

nacelle struts, and corrective action, if

necessary. That AD also gives an

optional modification of the vertical

chords, which ends the inspections.

This amendment requires the previously

optional modification. The actions

specified by this AD are intended to

prevent cracking of the vertical chords

adjacent to the lower spar fitting, which

could result in separation of the

diagonal brace load path. Continued

operation with a separated diagonal

brace load path increases loads on the

upper link, midspar fitting, and dual

side links, which could result in

separation of the strut and engine from

the airplane.

DATES: Effective July 27, 2001.

The incorporation by reference of

Boeing Alert Service Bulletin 747–

54A2201, dated September 28, 2000, as

listed in the regulations, was approved

previously by the Director of the Federal

Register as of December 13, 2000 (65 FR

70781, November 28, 2000).

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:

Tamara Anderson, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 2000–23–25,

amendment 39–11998 (65 FR 70781,

November 28, 2000), which is

applicable to certain Boeing Model 747–

100, 747–200, 747–300, 747SP, and

747SR series airplanes powered by Pratt

& Whitney JT9D–3 and JT9D–7 series

engines, was published in the Federal

Register on December 21, 2000 (65 FR

80388). The action proposed to continue

to require inspections of the vertical

chords of the aft torque bulkhead of the

outboard nacelle struts, and corrective

action, if necessary. The action also

proposed to require a previously

optional modification of the vertical

chords, which would end the

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 366

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

115 airplanes of U.S. registry will be

affected by this AD.

The detailed visual inspections that

are currently required by AD 2000–23–

25 take approximately 18 work hours

per airplane, at an average labor rate of

$60 per work hour. Based on these

figures, the FAA estimates that the cost

impact of these inspections on U.S.

operators is $124,200, or $1,080 per

airplane, per inspection cycle.

The ultrasonic and eddy current

inspections that are currently required

by AD 2000–23–25 take approximately

18 work hours per airplane, at an

average labor rate of $60 per work hour.

Based on these figures, the FAA

estimates that the cost impact of these

inspections on U.S. operators is

$124,200, or $1,080 per airplane, per

inspection cycle.

The new modification that is required

by this AD will take approximately 48

work hours per airplane, at an average

labor rate of $60 per work hour.

Required parts will cost approximately

$10,000 per airplane. Based on these

figures, the FAA estimates that the cost

impact of the new modification on U.S.

operators is $1,481,200, or $12,880 per

airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or new requirements of this

AD, 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 proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the 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

33460 Federal Register / Vol. 66, No. 121 / Friday, June 22, 2001 / Rules and Regulations

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 39–11998 (65 FR

70781, November 28, 2000), and by

adding a new airworthiness directive

(AD), amendment 39–12279, to read as

follows:

2001–12–23 Boeing: Amendment 39–12279.

Docket 2000–NM–354–AD. Supersedes

AD 2000–23–25, Amendment 39–11998.

Applicability: Model 747–100, 747–200,

747–300, 747SP, and 747SR series airplanes

powered by Pratt & Whitney JT9D–3 or JT9D–

7 series engines; as listed in Boeing Alert

Service Bulletin 747–54A2201, dated

September 28, 2000; 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

accordance with paragraph (e) 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 cracking of the vertical chords

adjacent to the lower spar fitting, which

could result in separation of the diagonal

brace load path and lead to separation of the

strut and engine from the airplane,

accomplish the following:

Restatement of Requirements of AD 2000–

23–25: Inspections

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

this AD, prior to the accumulation of 14,000

total flight cycles, or within 90 days after

December 13, 2000 (the effective date of AD

2000–23–25), whichever occurs later:

Accomplish paragraphs (a)(1) and (a)(2) of

this AD.

(1) Perform a detailed visual inspection to

detect cracking of the vertical chords of the

aft torque bulkhead of the outboard nacelle

struts, in accordance with Part 2 of the

Accomplishment Instructions of Boeing Alert

Service Bulletin 747–54A2201, dated

September 28, 2000. Thereafter, repeat this

inspection at intervals not to exceed 600

flight cycles until paragraph (d) of this AD is

accomplished.

(2) Perform surface eddy current and

ultrasonic inspections to detect cracking of

the vertical chords of the aft torque bulkhead

of the outboard nacelle struts, in accordance

with Part 3 of the Accomplishment

Instructions of Boeing Alert Service Bulletin

747–54A2201, dated September 28, 2000.

Thereafter, repeat these inspections at

intervals not to exceed 1,200 flight cycles

until paragraph (d) of this AD is

accomplished.

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.’’

Optional Compliance Time

(b) If Boeing Service Letter 747–54–055,

dated April 24, 1998, was accomplished on

the airplane during the modification of the

nacelle strut in accordance with AD 95–10–

16, amendment 39–9233: Accomplishment of

the initial inspection in paragraph (a) of this

AD may be deferred until 3,000 flight cycles

after accomplishment of the service letter.

Repair

(c) If any cracking is detected during any

inspection or modification required by this

AD: Prior to further flight, repair in

accordance with a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA; or in accordance with data

meeting the type certification basis of the

airplane approved by a Boeing Company

Designated Engineering Representative 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.

New Requirements of this AD: Modification

(Terminating Action)

(d) Within 4 years after the effective date

of this AD, do the modification of the vertical

chords of the aft torque bulkhead of the

outboard nacelle struts according to Part 4 of

Boeing Alert Service Bulletin 747–54A2201,

dated September 28, 2000. After this

modification, stop the repetitive inspections

required by paragraph (a) of this AD.

Alternative Methods of Compliance

(e) 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

(f) 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

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

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–54A2201, dated September 28,

2000. The incorporation by reference of that

document was approved previously by the

Director of the Federal Register as of

December 13, 2000 (65 FR 70781, November

28, 2000). 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.

Effective Date

(h) This amendment becomes effective on

July 27, 2001.

Issued in Renton, Washington, on June 14,

2001.

Vi L. Lipski,

Manager, Transport Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 01–15572 Filed 6–21–01; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–322–AD; Amendment

39–12278; AD 2001–12–22]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–9–81, –82, –83, and

–87 Series Airplanes, and MD–88

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.