Federal Register / Vol. 65, No. 12 / Wednesday, January 19, 2000 / Rules and Regulations 2861

(3) Inspect for cracks, bulges, pinholes, or

corrosion on the elbow (manifold) pipe, and

if any of this damage is found, replace the

elbow pipe.

(c) Visually inspect each wye duct beneath

the turbocharger for leakage, stains, cracks, or

pinholes, and, if damaged, repair or replace.

Carefully inspect the hard-to-see area

between the duct and firewall.

(1) Carefully inspect the turbocharger and

waste-gate flanges and welded seams

between the ducts and the firewall for

evidence of exhaust stains on the wye or the

firewall, bulges, cracks, or pinholes.

(2) If exhaust stains, bulges, cracks or

pinholes are found, repair or replace the

damaged part.

Pressure Test

(a) Pressurize the exhaust system with air

regulated to 20 PSI or below.

(b) Apply this air pressure to the tailpipe.

Fabricate shop fixtures as required to

accomplish this.

(c) Seal off the waste-gate pipe.

(d) Check the tailpipe, elbow pipes and the

wye duct for leaks by spraying leak check

fluid (bubbling) on these parts and looking

for the appearance of bubbles. Some air

leakage is normal at the joints and flanges,

but none should be seen anywhere else.

(e) Pay special attention to any weld

repairs, and various hard-to-see areas

described previously.

(f) If the tailpipes, elbow pipes, or the wye

ducts fail the pressure test, repair or replace

the distressed component.

(m) This amendment becomes effective on

February 15, 2000.

Issued in Kansas City, Missouri, on January

10, 2000.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 00–951 Filed 1–18–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–209–AD; Amendment

39–11515; AD 2000–01–17]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model MD–90 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model MD–90 series airplanes,

that requires a one-time detailed visual

inspection to detect fatigue cracking of

certain longerons and the attaching

frames of the lower left nose; and repair,

if necessary. This amendment also

requires installation of a preventive

modification. This amendment is

prompted by several reports of fatigue

cracking of certain longerons and the

attaching frames. The actions specified

by this AD are intended to prevent such

fatigue cracking, which could result in

reduced structural integrity of the

fuselage, and consequent loss of

pressurization of the airplane.

DATES: Effective February 23, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

23, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Aircraft

Group, Long Beach Division, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). 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,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Carl

Fountain, Aerospace Engineer, Airframe

Branch, ANM–120L; FAA, Los Angeles

Aircraft Certification Office, 3960

Paramount Boulevard, Lakewood,

California 90712; telephone (562) 627–

5222; fax (562) 627–5210.

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 McDonnell

Douglas Model MD–90 series airplanes

was published in the Federal Register

on October 27, 1999 (64 FR 57789). That

action proposed to require a one-time

detailed visual inspection to detect

fatigue cracking of certain longerons and

the attaching frames of the lower left

nose; and repair, if necessary. That

action also proposed to require

installation of a preventive

modification.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to single

the comments received.

The commenter states that it has no

objection to the proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 7 airplanes

of the affected design in the worldwide

fleet. The FAA estimates that 6

airplanes of U.S. registry will be affected

by this AD.

It will take approximately 1 work

hour per airplane to accomplish the

required inspection, at an average labor

rate of $60 per work hour. Based on

these figures, the cost impact of the

inspection required by this AD on U.S.

operators is estimated to be $360, or $60

per airplane.

It will take approximately 6 work

hours per airplane to accomplish the

required modification, at an average

labor rate of $60 per work hour. Parts

will cost approximately $312 per

airplane. Based on these figures, the cost

impact of the modification required by

this AD on U.S. operators is estimated

to be $4,032, or $672 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed 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.

2862 Federal Register / Vol. 65, No. 12 / Wednesday, January 19, 2000 / Rules and Regulations

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:

2000–01–17 McDonnell Douglas:

Amendment 39–11515. Docket 99–NM–

209–AD.

Applicability: Model MD–90 series

airplanes, as listed in McDonnell Douglas

Service Bulletin MD90–53–004, dated August

20, 1998, 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 (b) 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 longerons 22

through 26 and the attaching frames, which

could result in reduced structural integrity of

the fuselage, and consequent loss of

pressurization of the airplane, accomplish

the following:

Inspection and Modification

(a) Prior to the accumulation of 40,000 total

landings, or within 24 months after the

effective date of this AD, whichever occurs

later: Perform a detailed visual inspection to

detect cracking of longerons 22 through 26

(inclusive) and the respective attaching

frames at station frames Y=160.000 and

Y=200.000 of the left lower nose, in

accordance with McDonnell Douglas Service

Bulletin MD90–53–004, dated August 20,

1998.

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.’’

(1) If no cracking is detected: Prior to

further flight, install clips and doublers

under the longeron flanges and shim the

longerons in accordance with the service

bulletin.

(2) If any cracking is detected: Prior to

further flight, repair the cracks and install

clips and doublers under the longeron

flanges and shim the longerons in accordance

with the service bulletin.

Alternative Methods of Compliance

(b) 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, Los

Angeles 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, Los Angeles ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Los Angeles ACO.

Special Flight Permits

(c) 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

(d) The actions shall be done in accordance

with McDonnell Douglas Service

Bulletin MD90–53–004, dated August 20,

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 Aircraft Group,

Long Beach Division, 3855 Lakewood

Boulevard, Long Beach, California 90846,

Attention: Technical Publications Business

Administration, Dept. C1–L51 (2–60). Copies

may be inspected at the FAA, Transport

Airplane Directorate, 1601 Lind Avenue,

SW., Renton, Washington; or at the FAA,

Transport Airplane Directorate, Los Angeles

Aircraft Certification Office, 3960 Paramount

Boulevard, Lakewood, California; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(e) This amendment becomes effective on

February 23, 2000.

Issued in Renton, Washington, on January

10, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–950 Filed 1–18–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–217–AD; Amendment

39–11516; AD 2000–01–18]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–8 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain McDonnell

Douglas Model DC–8 series airplanes,

that requires a one-time eddy current

conductivity test to determine the

material type of the lower cap of the

wing front spar; and modification of the

lower cap of the wing front spar, if

necessary. This amendment is prompted

by reports of stress corrosion cracking in

the forward tang of the lower caps of the

wing front spar. The actions specified

by this AD are intended to prevent such

stress corrosion cracking, which if not

corrected, could result in reduced

structural integrity of the wing.

DATES: Effective February 23, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of February

23, 2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Boeing Commercial Aircraft

Group, Long Beach Division, 3855

Lakewood Boulevard, Long Beach,

California 90846, Attention: Technical

Publications Business Administration,

Dept. C1–L51 (2–60). 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,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.