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.

Federal Register / Vol. 65, No. 12 / Wednesday, January 19, 2000 / Rules and Regulations 2863

FOR FURTHER INFORMATION CONTACT: Greg

DiLibero, Airframe Branch, ANM–120L,

FAA, Transport Airplane Directorate,

Los Angeles Aircraft Certification

Office, 3960 Paramount Boulevard,

Lakewood, California 90712–4137;

telephone (562) 627–5231; 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 DC–8 series airplanes

was published in the Federal Register

on October 27, 1999 (64 FR 57792). That

action proposed to require 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.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports 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 294

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

251 airplanes of U.S. registry will be

affected by this AD, that it will take

approximately 3 work hours per

airplane to accomplish the required

inspection, and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the AD

on U.S. operators is estimated to be

$45,180, or $180 per airplane.

The cost impact figure discussed

above is 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.

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:

2000–01–18 McDonnell Douglas:

Amendment 39–11516. Docket 99–NM–21–

AD.

Applicability: Model DC–8 series airplanes,

as listed in McDonnell Douglas Service

Bulletin DC8–57–030, Revision 05, dated

April 28, 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 (c) 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 stress corrosion cracking of the

lower cap of the wing front spar, which if not

corrected, could result in reduced structural

integrity of the wing, accomplish the

following:

(a) Within 48 months after the effective

date of this AD, perform a one-time eddy

current conductivity test to determine the

material type of the forward tang of the lower

cap of the front spar in the center section of

the wing, in accordance with McDonnell

Douglas Service Bulletin DC8–57–030,

Revision 05, dated April 28, 1998, or

Revision 04, dated August 17, 1995.

(1) If 7079–T6 aluminum is not found, no

further action is required by this AD.

(2) If any 7079–T6 aluminum is found,

within 48 months after the effective date of

this AD, modify the forward tang of the lower

cap of the front spar, in accordance with the

service bulletin.

(b) Accomplishment of the eddy current

conductivity test, and modification, if

necessary, specified in paragraph (a) of this

AD constitutes terminating action for the

repetitive inspection requirements of

paragraph (a) of AD 90–16–05, amendment

39–6614, as it applies to the inspections of

the forward tang of the lower cap of the front

spar specified in McDonnell Douglas Service

Bulletin DC8–57–030, Revision 3, dated

December 10, 1970.

Alternative Methods of Compliance

(c) 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 2: 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

(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 McDonnell Douglas Service Bulletin

DC8–57–030, Revision 05, dated April 28,

1998, or McDonnell Douglas Service Bulletin

DC8–57–030, Revision 04, dated August 17,

1995. 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

2864 Federal Register / Vol. 65, No. 12 / Wednesday, January 19, 2000 / Rules and Regulations

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

February 23, 2000.

Issued in Renton, Washington, on January

11, 2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–1119 Filed 1–18–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–47–AD; Amendment

39–11511; AD 2000–01–13]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT9D Series Turbofan Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Pratt & Whitney

JT9D series turbofan engines, that

currently requires revisions to the

Airworthiness Limitations Section

(ALS) of the manufacturer’s Instructions

for Continued Airworthiness (ICA) to

include required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure. This action

adds additional critical life-limited parts

for enhanced inspection. This

amendment is prompted by additional

focused inspection procedures for other

critical life-limited rotating engine parts

that have been developed by the

manufacturer. The actions specified by

this AD are intended to prevent critical

life-limited rotating engine part failure,

which could result in an uncontained

engine failure and damage to the

airplane.

DATES: Effective February 23, 2000.

ADDRESSES: The information referenced

in this AD may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Wego Wang, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803-5299; telephone (781) 238–7134,

fax (781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding (AD) 99–08–12,

Amendment 39–11118 (64 FR 17954,

April 13, 1999), that is applicable to

Pratt & Whitney (PW) JT9D series

turbofan engine was published in the

Federal Register on August 16, 1999 (64

FR 44446). That action proposed to

require revisions to the Time Limits

section in the Engine Manual (EM) for

certain Pratt & Whitney (PW) JT9D

series turbofan engines to include

required enhanced inspection of

selected critical life-limited parts at

each piece-part exposure.

Since the issuance of that AD,

additional focused inspection

procedures for other critical life-limited

rotating engine parts have been

developed by PW.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

Both commenters suggest having the

same format for the two tables in the

AD. One also suggests using the term

‘‘all’’ rather than individual part

numbers to simplify recordkeeping tasks

for the operators. The FAA concurs with

their suggestions, and has combined the

two tables into one and substituted the

word ‘‘all’’ rather than using specific

part numbers. .

No comments were received on the

economic analysis contained in the

proposed rules. Based on that analysis,

the FAA has determined that the annual

per engine cost of $60 does not create

a significant economic impact on small

entities.

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

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

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, 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 39–11118 (63 FR

40220, April 13, 1999), and by adding

a new airworthiness directive, to read as

follows:

AD 2000–01–13 Pratt & Whitney:

Amendment 39–11511 Docket No. 98–

ANE–47–AD. Supersedes AD 99–08–12,

Amendment 39–11118.

Applicability:

Pratt & Whitney (PW) JT9D–7, –7A, –7H,

–7AH, –7F, –7J, –20, –20J, –59A, –70A, –7Q,

–7Q3, –7R4D, –7R4D1, –7R4E, –7R4E1,

–7R4E4, –7R4G2, and –7R4H1 series turbofan

engines, installed on but not limited to

Boeing 747 and 767 series, McDonnell

Douglas DC–10 series, and Airbus Industrie

A300 and A310 airplanes.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 (c)

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. For all the fan

hubs and HPT disks listed in the following

tables, the focused inspections should shall

be conducted per the applicable documents.

To prevent critical life-limited rotating

engine part failure, which could result in an

uncontained engine failure and damage to

the airplane, accomplish the following: