This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

15429

Vol. 62, No. 62

Tuesday, April 1, 1997

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–257–AD]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of 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 action

would reduce the repetitive inspection

interval for all of the currently required

inspections, except for the x-ray

inspections. It also would revise the

terminating modification provision for

some airplanes. This proposal is

prompted by reports of cracks found

during the currently-required

inspections, which had progressed to

lengths greater than predicted. The

actions specified by the proposed 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: Comments must be received by

May 9, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

257–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Lockheed Aeronautical Systems

Support Company, Field Support

Department, Dept. 693, Zone 0755, 2251

Lake Park Drive, Smyrna, Georgia

30080. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Atlanta Aircraft

Certification Office, Small Airplane

Directorate, Campus Building, 1701

Columbia Avenue, Suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7367; fax (404) 305–7348.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–NM–257–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

96–NM–257–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On March 28, 1996, the FAA issued

AD 96–07–13, amendment 39–9563 (61

FR 16379, April 15, 1996), applicable to

all Lockheed Model L–1011–385 series

airplanes. That AD requires repetitive

visual, x-ray, eddy current, and

ultrasonic 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. It also provides for

modification of the rear spar upper and

lower caps between Inner Wing Station

(IWS) 228 and 346 as terminating action

for the requirements of the AD.

AD 96–07–13 was prompted by

reports of fatigue cracking that occurred

in these areas. The requirements of that

AD are intended to ensure that fatigue

cracking is detected and corrected in a

timely manner. Such cracking, if not

corrected, could lead to rupture of the

rear spar and, consequently, result in

extensive damage to the wing and

spillage of fuel.

Actions Since Issuance of Previous Rule

Since the issuance of AD 96–07–13,

the FAA has received reports indicating

that fatigue cracks detected during

inspections performed in accordance

with that AD had progressed to lengths

greater than predicted. One finding

indicated that a crack apparently had

grown substantially during the

repetitive inspection period. These new

data indicate that, in order to detect and

correct the subject fatigue cracking

before it can progress to critical lengths,

the currently required inspections must

be performed more frequently.

Additionally, the manufacturer has

notified the FAA that the modification

of the rear spar upper and lower caps on

Model L–1011–385–3 airplanes, which

was described in Part I of Lockheed

Service Bulletin 093–57–203, Revision

4, dated March 27, 1995, has been

superseded by a web replacement that is

described in Lockheed Service Bulletin

093–57–215.
15430 Federal Register / Vol. 62, No. 62 / Tuesday, April 1, 1997 / Proposed Rules

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Lockheed Service Bulletin 093–57–203,

Revision 5, dated April 22, 1996, which

describes procedures for conducting

repetitive inspections to detect fatigue

cracking in the inboard web periphery

from IWS 346 to IWS 228. It

recommends that the inspections be

repeated at shorter intervals than those

recommended in Revision 4 of this

service bulletin (dated March 27, 1995).

The shorter intervals will ensure that

cracking is detected in a more timely

manner.

Additionally, Revision 5 does not

contain procedures for the modification

of the rear spar upper and lower caps for

Model L–1011–385–3 airplanes, which

was contained in Revision 4. That

modification has been revised, and the

procedures for it are now contained in

Lockheed L–1011 Service Bulletin 093–

57–215, dated April 11, 1996.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other products of this same

type design, the proposed AD would

supersede AD 96–07–13. It would

continue to require the same 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.

However, except for the currently

required x-ray inspections, these

inspections would be required to be

repeated at shorter intervals. These

actions would be required to be

accomplished in accordance with

Revision 5 of Lockheed Service Bulletin

093–57–203, described previously.

This new proposed AD would

continue to provide for terminating

action for the repetitive inspections, as

was provided in AD 96–07–13.

However, terminating action for Model

L–1011–385–3 airplanes would be

required to be accomplished in

accordance with the procedures

specified in Lockheed L–1011 Service

Bulletin 093–57–215.

Cost Impact

There are approximately 236

Lockheed Model L–1011–385 series

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

118 airplanes of U.S. registry would be

affected by this proposed AD.

The inspections that are proposed in

this AD action would 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.

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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

Is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting 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.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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), to

read as follows:

Lockheed: 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

otherwise 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 5, dated

April 22, 1996.
Federal Register / Vol. 62, No. 62 / Tuesday, April 1, 1997 / Proposed Rules 15431

(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 5 of the Lockheed service

bulletins. 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 5 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 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

• 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 5, dated April 22, 1996; 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 5, dated April 22, 1996.

(1) If no cracking is found: Repeat the

inspections and follow-on actions in

accordance with the times specified in Table

I 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 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 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

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.

Issued in Renton, Washington, on March

25, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8125 Filed 3–31–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–194–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A310 and A300–600

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to

certain Airbus Industrie Model A310

and A300–600 series airplanes. This

proposal would require modifying the

rudder trim switch and control knob.

This proposal is prompted by reports of

in-flight uncommanded rudder trim

activation due to inadvertent activation

of the rudder trim control switch, failure

of the switch, or incorrect installation of

the switch. The actions specified by the

proposed AD are intended to prevent

such uncommanded rudder trim

activation, which could result in

uncommanded yaw/roll excursions and

consequent reduced controllability of

the airplane.

DATES: Comments must be received by

May 9, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

194–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tom

Groves, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–1503; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments