63792 Federal Register / Vol. 65, No. 207 / Wednesday, October 25, 2000 / Rules and Regulations

Issued in Renton, Washington, on October

17, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27121 Filed 10–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–345–AD; Amendment

39–11943; AD 2000–21–11]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BH.125, DH.125, and HS.125

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Raytheon Model

DH.125–1A, –3A, and –400A series

airplanes, that currently requires a onetime inspection to detect scoring of the

upper fuselage skin around the

periphery of the cockpit canopy blister

interface, and repair, if necessary. This

amendment expands the applicability of

the existing AD to include additional

airplanes, and requires that the actions

be accomplished in accordance with

revised service information for the

newly added airplanes. This

amendment is prompted by additional

reports indicating that scoring has been

detected on the upper fuselage skin

around the periphery of the cockpit

canopy blister interface. The actions

specified by this AD are intended to

detect and correct scoring of the upper

fuselage skin around the periphery of

the cockpit canopy blister interface,

which could result in reduced structural

integrity of the fuselage, and consequent

cabin depressurization.

DATES: Effective November 29, 2000.

The incorporation by reference of

Raytheon Aircraft Service Bulletin SB

53–93, Revision 2, dated April 2000, as

listed in the regulations, is approved by

the Director of the Federal Register as of

November 29, 2000.

The incorporation by reference of

Raytheon Aircraft Service Bulletin SB

53–93, dated May 16, 1996, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of June 6, 1997 (62 FR 24013,

May 2, 1997).

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Commercial Service Department, P.O.

Box 85, Wichita, Kansas 67201–0085.

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 FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: T.N.

Baktha, Aerospace Engineer, Airframe

Branch, ACE–118W, FAA, Wichita

Aircraft Certification Office, 1801

Airport Road, Room 100, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone (316) 946–4155; fax (316)

946–4407.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 97–09–12,

amendment 39–10008 (62 FR 24013,

May 2, 1997), which is applicable to all

Raytheon Model DH.125–1A, –3A, and

–400A series airplanes, was published

in the Federal Register on June 16, 2000

(65 FR 37723). The action proposed to

continue to require a one-time

inspection to detect scoring of the upper

fuselage skin around the periphery of

the cockpit canopy blister interface, and

repair, if necessary. The action also

proposed to expand the applicability of

the existing AD to include additional

airplanes and to require that the actions

be accomplished in accordance with

revised service information for the

newly added airplanes.

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 290

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

200 airplanes of U.S. registry will be

affected by this AD.

The actions that are currently

required by AD 97–09–12 and retained

in this AD take approximately 4 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 $48,000, or

$240 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. The cost impact

figures discussed in AD rulemaking

actions represent only the time

necessary to perform the specific actions

actually required by the AD. These

figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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.

Federal Register / Vol. 65, No. 207 / Wednesday, October 25, 2000 / Rules and Regulations 63793

§ 39.13 [Amended]

2. Section 39.13 is amended by

removing amendment 39–10008 (62 FR

24013, May 2, 1997), and by adding a

new airworthiness directive (AD),

amendment 39–11943, to read as

follows:

2000–21–11 Raytheon Aircraft Company:

Amendment 39–11943. Docket 99–NM–

345–AD. Supersedes AD 97–09–12,

Amendment 39–10008.

Applicability: Model DH.125, BH.125, and

HS.125 series airplanes, as listed in Raytheon

Aircraft Service Bulletin SB 53–93, Revision

2, dated April 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 detect and correct scoring of the upper

fuselage skin around the periphery of the

cockpit canopy blister interface, which could

result in reduced structural integrity of the

fuselage skin, and consequent cabin

depressurization; accomplish the following:

Restatement of the Requirements of AD 97–

09–12:

(a) For Model DH.125–1A, –3A, and –400A

series airplanes, as identified in Raytheon

Aircraft Service Bulletin SB 53–93, dated

May 16, 1996: Within 90 days after June 6,

1997 (the effective date of AD 97–09–12,

amendment 39–10008), perform a one-time

detailed visual inspection to detect scoring of

the upper fuselage skin around the periphery

of the cockpit canopy blister interface, in

accordance with the service bulletin.

(b) If no scoring is detected during the

inspection required by paragraph (a) of this

AD, no further action is required by this AD.

(c) If any scoring is detected during the

inspection required by paragraph (a) of this

AD, prior to further flight, determine the

maximum location and details of each score,

including the edge distance and material

thickness, in accordance with Raytheon

Aircraft Service Bulletin SB 53–93, dated

May 16, 1996.

(1) If any scoring is found that is within the

limits specified in the service bulletin, prior

to further flight, repair in accordance with

the service bulletin.

(2) If any scoring is found that is outside

the limits specified in the service bulletin,

prior to further flight, repair in accordance

with a method approved by the Manager,

Wichita Aircraft Certification Office (ACO),

FAA.

New Requirements of this AD:

(d) For airplanes identified in Raytheon

Aircraft Service Bulletin SB 53–93, Revision

2, dated April 2000, and not previously

identified in paragraph (a) of this AD: Within

90 days after the effective date of this AD,

perform a one-time detailed visual inspection

to detect scoring of the upper fuselage skin

around the periphery of the cockpit canopy

blister interface, in accordance with

Raytheon Aircraft Service Bulletin SB 53–93,

Revision 2, dated April 2000.

(1) If no scoring is detected during the

inspection required by paragraph (d) of this

AD, no further action is required by this AD.

(2) If any scoring is detected during the

inspection required by paragraph (d) of this

AD, prior to further flight, determine the

location and details of each score, including

the edge distance and material thickness, in

accordance with the service bulletin.

(i) If any scoring is found that is within the

limits specified in the service bulletin, prior

to further flight, repair in accordance with

the service bulletin.

(ii) If any scoring is found that is outside

the limits specified in the service bulletin,

prior to further flight, repair in accordance

with a method approved by the Manager,

Wichita ACO.

Note 2: Any inspections and repairs

accomplished prior to the effective date in

accordance with Raytheon Service Bulletin

SB 53–93, Revision 1, dated April 1999, are

considered acceptable for compliance for the

applicable actions required by 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, Wichita

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permits

(f) Special flight permits may be issued in

accordance with §§ 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 paragraphs (c)(2)

and (d)(2)(ii) of this AD, the actions shall be

done in accordance with Raytheon Aircraft

Service Bulletin SB 53–93, dated May 16,

1996; and Raytheon Aircraft Service Bulletin

SB 53–93, Revision 2, dated April 2000; as

applicable.

(1) The incorporation by reference of

Raytheon Aircraft Service Bulletin SB 53–93,

Revision 2, dated April 2000, 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

Raytheon Aircraft Service Bulletin SB 53–93,

dated May 16, 1996, was approved

previously by the Director of the Federal

Register as of June 6, 1997 (62 FR 24013, May

2, 1997).

(3) Copies may be obtained from Raytheon

Aircraft Company, Commercial Service

Department, P.O. Box 85, Wichita, Kansas

67201–0085. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington; or at

the FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; 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

November 29, 2000.

Issued in Renton, Washington, on October

17, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–27120 Filed 10–24–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NE–47–AD; Amendment

39–11947; AD 2000–22–01]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney PW4000 Series Turbofan

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Pratt & Whitney

(PW) PW4000 series turbofan engines

that are equipped with the high pressure

compressor (HPC) cutback stator (CBS)

configuration and that are used on

Boeing 747, Boeing 767, and McDonnell

Douglas MD–11 series airplanes. This

action requires Operators to limit the

number of engines with the HPC CBS

configuration to one per airplane, and

prohibits installation of engines with

HPC modules modified after the

effective date of this AD to incorporate

the HPC CBS configuration. This

amendment is prompted by reports of

HPC surges in engines that have the

HPC CBS configuration. The actions

specified in this AD are intended to

prevent a multiple-engine power loss

due to HPC surges, which could result

in engine power loss at a critical phase

of flight such as takeoff or climb.