Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations 39079

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–66–AD; Amendment

39–11799; AD 2000–12–21]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

Equipped with Pratt & Whitney PW4000

Series Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 747–

400 series airplanes. The AD requires

installation of a modification of the

thrust reverser control and indication

system and wiring on each engine; and

repetitive functional tests of that

installation to detect discrepancies, and

repair, if necessary. This amendment is

prompted by the results of a safety

review, which revealed that in-flight

deployment of a thrust reverser could

result in a significant reduction in

airplane controllability. The actions

specified by this AD are intended to

ensure the integrity of the fail-safe

features of the thrust reverser system by

preventing possible failure modes,

which could result in inadvertent

deployment of a thrust reverser during

flight, and consequent reduced

controllability of 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 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:

Larry Reising, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Transport Airplane Directorate, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2683;

fax (425) 227–1181.

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 Boeing

Model 747–400 series airplanes was

published in the Federal Register on

December 28, 1999 (64 FR 72579). That

action proposed to require installation

of a modification of the thrust reverser

control and indication system and

wiring on each engine; and repetitive

functional tests of that installation to

detect discrepancies, and repair, 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.

Support for the Proposed Rule

One commenter states that it has no

objection to the proposed rule and does

not anticipate any adverse impact due to

the proposed rule.

Request to Reference Previous

Revisions of Service Bulletins

Two commenters request that the

FAA revise the proposed rule to

reference Boeing Service Bulletin 747–

78–2155, Revision 1, dated January 30,

1997, as an acceptable source of service

information for accomplishment of the

actions specified in paragraph (a)(1) of

the proposed rule. [The proposed rule

referenced Revision 2 of Boeing Service

Bulletin 747–78–2155, dated November

5, 1998, as the appropriate source of

service information for the actions

specified in paragraph (a)(1).] One of the

commenters also requests that the FAA

revise paragraph (a)(2)(iii) of the

proposed rule to reference Boeing

Service Bulletin 747–78–2154, Revision

1, dated November 2, 1995, and

Revision 2, dated October 31, 1996, as

acceptable sources of service

information. [The proposed rule

referenced Revision 3 of Boeing Service

Bulletin 747–78–2154, dated December

11, 1997, as the appropriate source of

service information for the actions

specified in paragraph (a)(2)(iii).] One of

the commenters, an operator, states that

it has already modified its Model 747–

400 series airplanes using Boeing

Service Bulletin 747–78–2155, Revision

1. The other commenter notes that the

earlier issues of the service bulletins are

similar to the revisions referenced in the

proposed rule, which only made

corrections of typographical errors and

clarifications of illustrations.

The FAA concurs with the

commenters’ requests. The FAA has

reviewed and approved Boeing Service

Bulletins 747–78–2155, Revision 1, and

747–78–2154, Revisions 1 and 2, and

finds that they are substantially similar

to the later revisions of the service

bulletins referenced in the proposed

rule. Accordingly, two new notes (Note

2 and Note 3) have been added to this

final rule to give credit for

accomplishment of the actions in

paragraphs (a)(1) and (a)(2)(iii) of this

AD prior to the effective date of this AD

in accordance with the earlier revisions

of the service bulletins described

previously.

Request To Specify Terminating Action

One commenter requests that the

proposed rule be revised to specify that,

for airplanes having line numbers 1067

and higher on which the intent of

Boeing Service Bulletin 747–78–2155

was accomplished during production,

this AD is terminating action for AD 94–

15–05, amendment 39–8976 (59 FR

37655, July 25, 1994). The commenter

states that this is not clear in the

proposed rule.

Because paragraph (a) of this AD does

not apply to airplanes having line

numbers 1067 and higher, the FAA

infers that the commenter is requesting

that paragraph (b) of the proposed rule

be revised to state that accomplishment

of the functional test in that paragraph

constitutes terminating action for the

actions required by AD 94–15–05. The

FAA concurs with the commenter’s

request. Paragraph (a) of AD 94–15–05

requires various inspections and

functional tests of the thrust reverser

control and indication system, and

correction of any discrepancy found, on

Boeing Model 747–400 series airplanes

powered by Pratt & Whitney PW4000

series engines. For airplanes having line

numbers 1067 and higher on which the

intent of Boeing Service Bulletin 747–

78–2155 was accomplished during

production, accomplishment of the

repetitive functional tests required by

paragraph (b) of this AD constitutes

terminating action for the repetitive

inspections and functional tests

required by paragraph (a) of AD 94–15–

05. Therefore, a new paragraph (c) has

been added to this AD to state this, and

all subsequent paragraphs have been

relettered accordingly.

Explanation of Additional Change to

Proposed Rule

Paragraph (b) of the proposed rule

contains an incorrect reference. That

paragraph specifies that any

discrepancy detected during the

functional test must be corrected in

accordance with procedures described

in the Boeing 747 Airplane Maintenance

39080 Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations

Manual. The correct source of service

information for the accomplishment of

corrective actions is the Boeing 747–400

Airplane Maintenance Manual.

Paragraph (b) of this final rule has been

revised 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 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 177 Model

747–400 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 53 airplanes of U.S.

registry will be affected by this AD.

For airplanes identified in Boeing

Service Bulletin 747–78–2155, Revision

2 (45 airplanes), it takes approximately

510 work hours per airplane to

accomplish the required installation, at

an average labor rate of $60 per work

hour. Required parts will be provided

by the manufacturer at no cost to the

operators. Based on these figures, the

cost impact of the installation required

by this AD on U.S. operators is

estimated to be $1,377,000, or $30,600

per airplane.

For all airplanes (53 airplanes) it will

take approximately 2 work hours per

airplane to accomplish the required

functional test, at an average labor rate

of $60 per work hour. Based on these

figures, the cost impact of the functional

test required by this AD on U.S.

operators is estimated to be $6,360, or

$120 per airplane, per test cycle.

The cost impact figures discussed

below refer to actions in other service

bulletins for the airplanes identified in

Boeing Service Bulletin 747–78–2155,

Revision 2 (affects 45 U.S.-registered

airplanes), that must be accomplished

prior to or concurrent with the

installation specified in Boeing Service

Bulletin 747–78–2155, Revision 2.

It will take approximately 3 work

hours per airplane to accomplish the

central maintenance computer system

modification, at an average labor rate of

$60 per work hour. Required parts will

be provided by the manufacturer at no

cost to the operators. Based on these

figures, the cost impact of this

modification is estimated to be $8,100,

or $180 per airplane.

It will take approximately 2 work

hours per airplane to accomplish the

changes to the integrated display

system, at an average labor rate of $60

per work hour. Required parts will be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of this modification is

estimated to be $5,400, or $120 per

airplane.

It will take approximately 346 work

hours per airplane to accomplish wiring

provisions for the thrust reverser sync

locks, at an average labor rate of $60 per

work hour. Required parts will be

provided by the manufacturer at no cost

to the operators. Based on these figures,

the cost impact of this modification is

estimated to be $934,200, or $20,760 per

airplane.

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

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:

2000–12–21 Boeing: Amendment 39–11799.

Docket 99–NM–66–AD.

Applicability: Model 747–400 series

airplanes equipped with Pratt & Whitney

PW4000 series engines; 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 (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 inadvertent deployment of a

thrust reverser during flight and consequent

reduced controllability of the airplane,

accomplish the following:

Modifications

(a) For airplanes identified in Boeing

Service Bulletin 747–78–2155, Revision 2,

dated November 5, 1998: Accomplish the

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

of this AD at the times specified in those

paragraphs. Accomplishment of these actions

constitutes terminating action for the

inspections and tests required by paragraph

(a) of AD 94–15–05, amendment 39–8976.

(1) Within 36 months after the effective

date of this AD: Install an additional locking

system on each engine thrust reverser in

accordance with the Accomplishment

Instructions of Boeing Service Bulletin 747–

78–2155, Revision 2, dated November 5,

1998.

Note 2: Installations accomplished prior to

the effective date of this AD in accordance

with Boeing Service Bulletin 747–78–2155,

Revision 1, dated January 30, 1997, are

considered acceptable for compliance with

paragraph (a)(1) of this AD.

(2) Prior to or concurrent with the

installation required by paragraph (a)(1) of

this AD, accomplish the requirements of

paragraphs (a)(2)(i), (a)(2)(ii), and (a)(2)(iii) of

this AD:

(i) Modify the central maintenance

computer system hardware and software in

accordance with Boeing Service Bulletin

747–45–2016, Revision 1, dated May 2, 1996.

Federal Register / Vol. 65, No. 122 / Friday, June 23, 2000 / Rules and Regulations 39081

(ii) Modify the integrated display system

software in accordance with Boeing Service

Bulletin 747–31–2245, dated June 27, 1996.

(iii) Install the provisional wiring for the

locking system on the thrust reversers in

accordance with Boeing Service Bulletin

747–78–2154, Revision 3, dated December

11, 1997.

Note 3: Installations accomplished prior to

the effective date of this AD in accordance

with Boeing Service Bulletin 747–78–2154,

Revision 1, dated November 2, 1995, and

Revision 2, dated October 31, 1996, are

considered acceptable for compliance with

paragraph (a)(2)(iii) of this AD.

Repetitive Functional Tests

(b) Within 4,000 hours time-in-service after

accomplishment of paragraph (a) of this AD,

or production equivalent; or within 1,000

hours time-in-service after the effective date

of this AD, whichever occurs later: Perform

a functional test to detect discrepancies of

the additional locking system on each engine

thrust reverser, in accordance with Appendix

1 of this AD. Prior to further flight, correct

any discrepancy detected and repeat the

functional test of that repair, in accordance

with the procedures described in the Boeing

747–400 Airplane Maintenance Manual.

Repeat the functional test thereafter at

intervals not to exceed 4,000 hours time-inservice.

Terminating Action: Airplanes Having Line

Numbers 1067 and Higher

(c) For airplanes having line numbers 1067

and higher on which the intent of Boeing

Service Bulletin 747–78–2155, Revision 2,

dated November 5, 1998, was accomplished

during production: Accomplishment of the

repetitive functional tests required by

paragraph (b) of this AD constitutes

terminating action for the repetitive

inspections and functional tests required by

paragraph (a) of AD 94–15–05, amendment

39–8976.

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, Seattle

Aircraft Certification Office (ACO), 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, Seattle ACO.

Note 4: 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

(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) Except as provided by paragraph (b) of

this AD, the actions shall be done in

accordance with Boeing Service Bulletin

747–78–2155, Revision 2, dated November 5,

1998; Boeing Service Bulletin 747–45–2016,

Revision 1, dated May 2, 1996; Boeing

Service Bulletin 747–31–2245, dated June 27,

1996; or Boeing Service Bulletin 747–78–

2154, Revision 3, dated December 11, 1997;

as applicable. 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.

Effective Date

(g) This amendment becomes effective on

July 28, 2000.

Issued in Renton, Washington, on June 14,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–15545 Filed 6–22–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 00–ASO–9]

Amendment to Class D and Class E5

Airspace, Greenwood, MS

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action amends Class D

and E airspace at Greenwood—Leflore

Airport, Greenwood, MS. An Area

Navigation (RNAV) Runway (RWY) 18

Standard Instrument Approach

Procedure (SIAP) has been developed

for Greenwood, MS. As a result,

additional controlled airspace extending

upward from the surface and extending

upward from 700 feet Above Ground

Level (AGL) is needed to accommodate

the SIAP. This action also makes a

technical change by amending the name

of the VORTAC from Greenwood to

Sidon.

EFFECTIVE DATE: 0901 UTC, October 5,

2000.

FOR FURTHER INFORMATION CONTACT:

Nancy B. Shelton, Manager, Airspace

Branch, Air Traffic Division, Federal

Aviation Administration, P.O. Box

20636, Atlanta, Georgia 30320;

telephone (404) 305–5627.

SUPPLEMENTARY INFORMATION:

History

On April 19, 2000, the FAA proposed

to amend part 71 of the Federal Aviation

Regulations (14 CFR part 71) by

amending Class D and E airspace at

Greenwood—Leflore Airport,

Greenwood, MS. This action would

provide adequate Class D and E airspace

at the airport for the RNAV RWY 18

SIAP. Class D airspace designations are

published in Paragraph 5000, Class E4

airspace designations are published in

Paragraph 6004 and Class E5 airspace

designations are published in Paragraph

6005 of FAA Order 7400.9G, dated

September 1, 1999, and effective

September 16, 1999, which is

incorporated by reference in 14 CFR

71.1, dated September 1, 1999. The

Class D and E airspace designations

listed in this document will be

published subsequently in the Order.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments objecting to the proposal

were received.

The Rule

This amendment to Part 71 of the

Federal Aviation Regulations (14 CFR

part 71) amends Class D and E airspace

at Greenwood—Leflore Airport,

Greenwood, MS. This action also makes

a technical change by amending the

name of the VORTAC from Greenwood

to Sidon.

The FAA has determined that this

regulation only involves an established

boy of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. It, therefore, (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)

does not warrant preparation of a

regulatory evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it

is certified that this rule will not have

a significant economic impact on a

substantial number of small entities

under the criteria of the Regulatory

Flexibility Act.

List of Subjects in 14 CFR part 71

Airspace, Incorporated by reference,

Navigation (air).

Adoption of the Amendment

In consideration of the foregoing, the

Federal Aviation Administration

amends 14 CFR Part 71 as follows: