26966 Federal Register / Vol. 63, No. 94 / Friday, May 15, 1998 /Rules and Regulations

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–257–AD; Amendment

39–10526; AD 98–10–14]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to all Lockheed Model L–

1011–385 series airplanes, that currently

requires various types of inspections to

detect fatigue cracking of certain areas

of the rear spar caps, web, skin, and

certain fastener holes; and repair or

modification, if necessary. This

amendment reduces the repetitive

inspection interval for all of the

currently required inspections, except

for the X-ray inspections. It also revises

the terminating modification provision

for some airplanes. This amendment is

prompted by reports of cracks found

during the currently required

inspections, which had progressed to

lengths greater than predicted. The

actions specified by this AD are

intended to ensure that fatigue cracking

is detected and corrected in a timely

manner before it can lead to rupture of

the rear spar, extensive damage to the

wing, and spillage of fuel.

DATES: Effective June 19, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 19,

1998.

The incorporation by reference of

certain other publications, as listed in

the regulations, was approved

previously by the Director of the Federal

Register as of May 15, 1996 (61 FR

16379, April 15, 1996).

ADDRESSES: The service information

referenced in this AD may be obtained

from Lockheed Aeronautical Systems

Support Company (LASSC), Field

Support Department, Dept. 693, Zone

0755, 2251 Lake Park Drive, Smyrna,

Georgia 30080. 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, Small

Airplane Directorate, ACE–116A,

Atlanta Aircraft Certification Office,

1895 Phoenix Boulevard, suite 450,

Atlanta, Georgia; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Atlanta Aircraft Certification

Office, Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6067;

fax (770) 703–6097.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39)

by superseding AD 96–07–13,

amendment 39–9563 (61 FR 16379,

April 15, 1996), which is applicable to

all Lockheed Model L–1011–385 series

airplanes, was published in the Federal

Register on April 1, 1997 (62 FR 15429).

That action proposed to supersede AD

96–07–13 to continue to require various

types of inspections to detect fatigue

cracking of certain areas of the rear spar

caps, web, skin, and certain fastener

holes; and repair or modification, if

necessary. That action also proposed to

reduce the repetitive inspection interval

for all of the currently required

inspections, except for the X-ray

inspections. Additionally, it proposed to

revise the terminating modification

provision for some airplanes.

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 Proposal

Three commenters support the

proposed rule.

Require Compliance With New Service

Information

One commenter, the manufacturer,

requests that the proposal require

compliance with Revision 6 of

Lockheed L–1011 Service Bulletin 093–

57–203, rather than Revision 5, as cited

in the proposal. The manufacturer

advises that Revision 6 of the service

bulletin contains significant

clarification and simplifies the proposed

inspections, which will enable operators

to perform the proposed inspections in

a correct and efficient manner. Further,

the manufacturer notes that Revision 6

of the service bulletin contains no

additional procedures to be

accomplished, and therefore would pose

no additional burden on any operator.

The FAA concurs. Since the issuance

of the proposed rule, the FAA has

reviewed and approved Lockheed L–

1011 Service Bulletin 093–57–203,

Revision 6, dated August 18, 1997. The

FAA finds that accomplishment of

certain requirements of this AD in

accordance with Revision 5 of the

subject service bulletin adequately

addresses the unsafe condition.

Therefore, the FAA has revised the final

rule to require compliance in

accordance with Revision 6 of the

service bulletin.

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 change

previously described. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

There are approximately 236 Model

L–1011–385 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 118 airplanes of

U.S. registry will be affected by this AD.

The actions that are currently

required by AD 96–07–13 will take

approximately 64 work hours per

airplane to accomplish, at an average

labor rate of $60 per work hour. [This

work hour estimate assumes that X-ray

inspections are done of both upper and

lower caps, and that the ultrasonic

inspection indicates cracking in each of

five bolt holes (per wing), thus requiring

subsequent bolt hole eddy current

inspections to confirm crack findings.

The estimate includes inspections of

both wings.] Based on these figures, the

cost impact on U.S. operators of the

proposed inspection requirements of

this AD is estimated to be $453,120, or

$3,840 per airplane, per inspection

cycle. This new AD action adds no new

costs to affected operators.

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 substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism
Federal Register / Vol. 63, No. 94 / Friday, May 15, 1998 /Rules and Regulations 26967

implications to warrant the preparation

of a Federalism Assessment.

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

removing amendment 39–9563 (61 FR

16379, April 15, 1996), and by adding

a new airworthiness directive (AD),

amendment 39–10526, to read as

follows:

98–10–14 Lockheed: Amendment 39–

10526. Docket 96–NM–257–AD.

Supersedes AD 96–07–13, Amendment

39–9563.

Applicability: All Model L–1011–385–1, L–

1011–385–3, L–1011–385–1–14, and L–1011–

385–1–15 series airplanes; 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 rupture of the rear spar due to

the problems associated with fatigue

cracking, which could result in extensive

damage to the wing and fuel spillage,

accomplish the following:

Note 2: The inspections and follow-on

actions described in Lockheed L–1011

Service Bulletin 093–57–203 include:

—repetitive X-ray (radiographic) inspections;

—repetitive eddy current surface scan

inspections;

—bolt hole eddy current inspections at

various locations;

—repetitive ultrasonic inspections in

conjunction with eddy current surface scan

inspections (for certain airplanes); and

—repetitive low frequency eddy current ring

probe inspections.

(a) For airplanes on which the inspections

and follow-on actions required by AD 96–07–

13, amendment 39–9563, have been initiated

prior to the effective date of this AD: At the

times specified in Table I of Lockheed L–

1011 Service Bulletin 093–57–203, Revision

4, dated March 27, 1995; or within 6 months

after May 15, 1996 (the effective date of AD

96–07–13, amendment 39–9563), whichever

occurs later: Perform initial inspections and

various follow-on actions to detect cracking

in the areas specified in, at the times

indicated in, and in accordance with

Lockheed L–1011 Service Bulletin 093–57–

203, Revision 4, dated March 27, 1995, or

Revision 6, dated August 18, 1997.

(1) If no cracking is found, repeat the

repetitive inspections and follow-on actions

in accordance with Table I of the Lockheed

service bulletin. As of the effective date of

this AD, these actions shall be repeated at the

times specified only in accordance with

Table 1 of Revision 6 of the Lockheed service

bulletin. To avoid unnecessary grounding of

airplanes that are currently being inspected

in accordance with the schedule specified in

Revision 4 of the Lockheed service bulletin,

the next repeated action that is to be

accomplished after the effective date of this

AD shall be performed at the time specified

in Table I of Revision 6 of the Lockheed

service bulletin, or within 30 days after the

effective date of this AD, whichever occurs

later.

(2) If any finding of cracking is confirmed,

prior to further flight, accomplish paragraph

(a)(2)(i), (a)(2)(ii), or (a)(2)(iii) of this AD.

(i) Repair the cracked area in accordance

with a method approved by the Manager,

Atlanta Aircraft Certification Office (ACO),

FAA, Small Airplane Directorate. Thereafter,

perform the repetitive inspections and

follow-on actions as specified in paragraph

(a)(1) of this AD.

(ii) Repair the rear spar upper and lower

caps between IWS 228 and 346 in accordance

with the Lockheed Model L–1011 Structural

Repair Manual. Thereafter, perform the

repetitive inspections and follow-on actions

required by paragraph (a)(1) of this AD. Or

(iii) Modify the rear spar upper and lower

caps and web in accordance with the

applicable Lockheed service bulletin listed in

this paragraph, below. Accomplishment of

the modification constitutes terminating

action for the requirements of this AD.

—Lockheed L–1011 Service Bulletin 093–57–

184, Revision 7, dated December 6, 1994,

as amended by Change Notification 093–

57–184, R7–CN1, dated August 22, 1995; or

—Lockheed L–1011 Service Bulletin 093–57–

196, Revision 6, dated December 6, 1994,

as amended by Change Notification 093–

57–196, R6–CN1, dated August 22, 1995; or

—Lockheed L–1011 Service Bulletin 093–57–

215, dated April 11, 1996. Modification of

Model L–1011–385–3 airplanes must be

accomplished in accordance with this

service bulletin.

Note 3: Accomplishment of the

modification specified in paragraph (a)(2)(iii)

of this AD prior to the effective date of this

AD in accordance with the following

Lockheed service bulletins, as applicable, is

considered to be in compliance with this

paragraph:

• Lockheed L–1011 Service Bulletin 093–57–

184, Revision 6, dated October 28, 1991;

• Lockheed L–1011 Service Bulletin 093–57–

184, Revision 7, dated December 6, 1994;

• Lockheed L–1011 Service Bulletin 093–57–

196, Revision 5, dated October 28, 1991; or

• Lockheed L–1011 Service Bulletin 093–57–

196, Revision 6, dated December 6, 1994.

(b) For airplanes on which the inspections

and follow-on actions required by AD 96–07–

13, amendment 39–9563, have not been

initiated prior to the effective date of this AD:

At the times specified in Table I of Lockheed

L–1011 Service Bulletin 093–57–203,

Revision 6, dated August 18, 1997; or within

30 days after the effective date of this AD;

whichever occurs later: Perform initial

inspections and various follow-on actions to

detect cracking in the areas specified in, at

the times indicated in, and in accordance

with Lockheed L–1011 Service Bulletin 093–

57–203, Revision 6, dated August 18, 1997.

(1) If no cracking is found: Repeat the

inspections and follow-on actions in

accordance with the times specified in Table

I of Revision 6 of the Lockheed service

bulletin.

(2) If any finding of cracking is confirmed:

Prior to further flight, accomplish either

paragraph (b)(2)(i), (b)(2)(ii), or (b)(2)(iii) of

this AD.

(i) Repair the cracked area in accordance

with a method approved by the Manager,

Atlanta Aircraft Certification Office (ACO),

FAA, Small Airplane Directorate. Thereafter,

perform the repetitive inspections and

follow-on actions at the times specified in

Table 1 of Revision 6 of the Lockheed service

bulletin. Or

(ii) Repair the rear spar upper and lower

caps between IWS 228 and 346 in accordance

with the Lockheed Model L–1011 Structural

Repair Manual. Thereafter, perform the

repetitive inspections and follow-on actions

at the times specified in Table 1 of Revision

6 of the Lockheed service bulletin. Or

(iii) Modify the rear spar upper and lower

caps and web in accordance with paragraph

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

(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, Atlanta

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add
26968 Federal Register / Vol. 63, No. 94 / Friday, May 15, 1998 /Rules and Regulations

comments and then send it to the Manager,

Atlanta ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta ACO.

(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.

(e) Except as provided by paragraph

(a)(2)(i), (a)(2)(ii), (b)(2)(i), and (b)(2)(ii) of

this AD, the actions shall be done in

accordance with Lockheed L–1011 Service

Bulletin 093–57–203, Revision 4, dated

March 27, 1995; Lockheed L–1011 Service

Bulletin 093–57–203, Revision 6, dated

August 18, 1997; Lockheed L–1011 Service

Bulletin 093–57–184, Revision 7, dated

December 6, 1994, as amended by Change

Notification 093–57–184, R7-CN1, dated

August 22, 1995; Lockheed L–1011 Service

Bulletin 093–57–196, Revision 6, dated

December 6, 1994, as amended by Change

Notification 093–57–196, R6–CN1, dated

August 22, 1995; and Lockheed L–1011

Service Bulletin 093–57–215, dated April 11,

1996.

(1) The incorporation by reference of

Lockheed L–1011 Service Bulletin 093–57–

203, Revision 6, dated August 18, 1997; and

Lockheed L–1011 Service Bulletin 093–57–

215, dated April 11, 1996; 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

Lockheed L–1011 Service Bulletin 093–57–

184, Revision 7, dated December 6, 1994, as

amended by Change Notification 093–57–

184, R7–CN1, dated August 22, 1995;

Lockheed L–1011 Service Bulletin 093–57–

196, Revision 6, dated December 6, 1994, as

amended by Change Notification 093–57–

196, R6–CN1, dated August 22, 1995; and

Lockheed L–1011 Service Bulletin 093–57–

203, Revision 4, dated March 27, 1995, was

approved previously by the Director of the

Federal Register as of May 15, 1996 (61 FR

16379, April 15, 1996).

(3) Copies may be obtained from Lockheed

Aeronautical Systems Support Company

(LASSC), Field Support Department, Dept.

693, Zone 0755, 2251 Lake Park Drive,

Smyrna, Georgia 30080. Copies may be

inspected at the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW., Renton,

Washington; or at the FAA, Small Airplane

Directorate, Systems and Flight Test Branch,

ACE–116A, Atlanta Aircraft Certification

Office, One Crown Center, 1895 Phoenix

Boulevard, suite 450, Atlanta, Georgia; or at

the Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

June 19, 1998.

Issued in Renton, Washington, on May 7,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate Aircraft Certification Service.

[FR Doc. 98–12808 Filed 5–14–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–54–AD; Amendment

39–10525; AD 98–10–13]

RIN 2120–AA64

Airworthiness Directives; Dornier

Model 328–100 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dornier Model

328–100 series airplanes, that requires

modification of the aft avionic fan. This

amendment is prompted by issuance of

mandatory continuing airworthiness

information by a foreign civil

airworthiness authority. The actions

specified by this AD are intended to

prevent failure of the aft avionic fan due

to inadequate cooling airflow through

the fan housing, which could result in

failure of the avionics equipment.

DATES: Effective June 19, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 19,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from FAIRCHILD DORNIER, DORNIER

Luftfahrt GmbH, P.O. Box 1103, D–

82230 Wessling, Germany. 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:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

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 Dornier

Model 328–100 series airplanes was

published in the Federal Register on

March 12, 1998 (63 FR 12042). That

action proposed to require modification

of the aft avionic fan.

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

The FAA estimates that 50 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 9

work hours per airplane to accomplish

the required modification, at an average

labor rate of $60 per work hour. Based

on these figures, the cost impact of the

modification required by this AD on

U.S. operators is estimated to be

$27,000, or $540 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 substantial direct effects 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, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

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.