Federal Register / Vol. 65, No. 81 / Wednesday, April 26, 2000 / Rules and Regulations 24383

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 2: 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

(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 actions shall be done in accordance

with Raytheon Service Bulletin SB.54–1–

3815B, dated March 26, 1996; or Raytheon

Service Bulletin SB.54–1–3815B, Revision 1,

dated May 1998.

(1) The incorporation by reference of

Raytheon Service Bulletin SB.54–1–3815B,

Revision 1, dated May 1998, 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 Service Bulletin SB.54–1–3815B,

dated March 26, 1996, was approved

previously by the Director of the Federal

Register as of January 27, 1997 (61 FR 66878,

December 19, 1996).

(3) Copies may be obtained from Raytheon

Aircraft Company, Manager Service

Engineering, Hawker Customer Support

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, Small Airplane Directorate, Wichita

Aircraft Certification Office, 1801 Airport

Road, Room 100, Mid-Continent Airport,

Wichita, Kansas; or at the Office of the

Federal Register, 800 North Capitol Street,

NW., suite 700, Washington, DC.

(f) This amendment becomes effective on

May 31, 2000.

Issued in Renton, Washington, on April 14,

2000.

Charles D. Huber,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–9896 Filed 4–25–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–346–AD; Amendment

39–11701; AD 2000–08–15]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 777 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing 777 series

airplanes, that requires a one-time

inspection to detect cracking of the

fastener holes common to the upper

wing skins and trailing edge panels of

both wings, and corrective actions, if

necessary. This amendment also

requires coldwork of the fastener holes

and installation of new or serviceable

fasteners. This amendment is prompted

by a report indicating that fatigue cracks

have been found in the upper wing skin

of both wings. The actions specified by

this AD are intended to prevent fatigue

cracking of the upper wing skin, which

could result in reduced structural

integrity of the wing.

DATES: Effective May 31, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 31,

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: Stan

Wood, Aerospace Engineer, Airframe

Branch, ANM–120S, FAA, Transport

Airplane Directorate, Seattle Aircraft

Certification Office, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056;

telephone (425) 227–2772; 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 777

series airplanes was published in the

Federal Register on January 4, 2000 (65

FR 250). That action proposed to require

a one-time inspection to detect cracking

of the fastener holes common to the

upper wing skins and trailing edge

panels of both wings, and corrective

actions, if necessary. That action also

proposed to require coldwork of the

fastener holes and installation of new or

serviceable fasteners.

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 82 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 33

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 13 work hours per

airplane to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $216 per

airplane. Based on these figures, the cost

impact of the AD on U.S. operators is

estimated to be $32,868, or $996 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

24384 Federal Register / Vol. 65, No. 81 / Wednesday, April 26, 2000 / Rules and Regulations

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:

2000–08–15 Boeing: Amendment 39–11701.

Docket 99–NM–346–AD.

Applicability: Model 777 series airplanes

having line numbers 1 through 119 inclusive,

except line numbers 94, 102, 104, and 118;

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 fatigue cracking of the upper

wing skin, which could result in reduced

structural integrity of the wing, accomplish

the following:

Eddy Current Inspection of Fastener Holes

(a) Prior to the accumulation of 16,000 total

flight cycles or 40,000 total flight hours,

whichever occurs earlier, perform a one-time

eddy current inspection to detect cracking of

the fastener holes common to the upper wing

skins and trailing edge panels of both wings,

in accordance with Boeing Alert Service

Bulletin 777–57A0022, dated August 26,

1999.

Rework and Re-Inspection of Fastener Hole

(b) If any cracking is detected during the

inspection required by paragraph (a) of this

AD, prior to further flight, oversize the

fastener hole and perform additional eddy

current inspections to detect cracking of the

fastener holes until all cracking is no longer

detectable by means of eddy current

inspection. Perform the actions in accordance

with Boeing Alert Service Bulletin 777–

57A0022, dated August 26, 1999. Prior to

further flight, oversize the fastener hole an

additional 1/32-inch minimum and measure

the starting hole diameter and edge margin of

the fastener hole, in accordance with the alert

service bulletin.

(1) If the fastener hole diameter or the edge

margin of any fastener hole is not within the

limits specified in the alert service bulletin,

prior to further flight, repair in accordance

with a method approved by the Manager,

Seattle Aircraft Certification Office (ACO),

FAA, Transport Airplane Directorate, or a

Boeing Company Designated Engineering

Representative who has been authorized by

the FAA to make such findings. For a repair

method to be approved by the Manager,

Seattle ACO, as required by this paragraph,

the Manager’s approval letter must

specifically reference this AD.

(2) If the fastener hole diameter and edge

margin of all the fastener holes are within the

limits specified in the alert service bulletin,

prior to further flight, accomplish the

requirements of paragraph (c) of this AD.

Coldwork of Fastener Holes

(c) If no cracking is detected during the

eddy current inspection required by

paragraph (a), or the fastener hole diameter

and edge margin of all the fastener holes are

within the limits required by paragraph (b) of

this AD, prior to further flight, coldwork the

fastener holes and install new or serviceable

fasteners, in accordance with Boeing Alert

Service Bulletin 777–57A0022, dated August

26, 1999.

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

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 2: 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)(1)

of this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 777–57A0022, dated August 26,

1999. 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.

(g) This amendment becomes effective on

May 31, 2000.

Issued in Renton, Washington, on April 18,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–10160 Filed 4–25–00; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–253–AD; Amendment

39–11703; AD 2000–08–17]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–100, –200, –300, –400, and

–500 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Boeing Model 737–

100, –200, –300, –400, and –500 series

airplanes, that requires repetitive

inspections to detect damage of certain

taxi light assemblies, and replacement

with a new or serviceable part, if

necessary. This AD also requires

eventual replacement of certain taxi

light assemblies with improved parts,

which constitutes terminating action for

the repetitive inspections. This

amendment is prompted by a report that

a damaged taxi light detached from an

airplane and was ingested into the

airplane engines. The actions specified

by this AD are intended to prevent

damage to the taxi light assembly,

which could result in detachment of the

taxi light assembly from the airplane,

ingestion of taxi light debris into an

engine, and consequent loss of thrust

from one or both engines.

EFFECTIVE DATE: May 31, 2000.

ADDRESSES: Information pertaining to

this amendment may be examined at the

Federal Aviation Administration (FAA),

Transport Airplane Directorate, Rules

Docket, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

David Herron, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2672; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to