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
15432 Federal Register / Vol. 62, No. 62 / Tuesday, April 1, 1997 / Proposed Rules

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–194–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–194–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain Airbus

Industrie Model A310 and A300–600

series airplanes. The DGAC advises it

received reports indicating that

uncommanded rudder trim activation

occurred during flight on these

airplanes. These events were attributed

to the following causes:

• Unintentional activation of the

rudder trim when documentation was

inadvertently placed against the control

knob;

• Failure of the rudder trim control

switch on panel 408VU; or

Incorrect installation of the rudder

trim control switch.

Uncommanded activation of the

rudder trim, if not corrected, could lead

to uncommanded yaw/roll excursions

and consequent reduced controllability

of the airplane.

Explanation of Relevant Service

Information

Airbus Industrie has issued the

following service bulletins that describe

procedures to modify the rudder trim

switch and control knob:

• Service Bulletin A300–27–6022,

Revision 2, dated August 28, 1995 (for

Model A300–600 series airplanes).

• Service Bulletin A300–27–6027,

Revision 2, dated August 22, 1995; and

Revision 3, dated March 13, 1996 (for

Model A300–600 series airplanes).

• Service Bulletin A310–27–2058,

Revision 2, dated August 28, 1995 (for

Model A310 series airplanes).

• Service Bulletin A310–27–2071,

Revision 2, dated August 22, 1995; and

Revision 3, dated March 13, 1996 (for

Model A310 series airplanes).

The modification procedures include

replacing the rudder trim switch,

control knob, and associated wires with

new components and wiring;

reinstalling panel 408VU; and

conducting tests to ensure proper

operation of the assembly. The

accomplishment of these modifications

will preclude uncommanded rudder

trim activation.

The DGAC classified the previously

described service bulletins as

mandatory and issued French

airworthiness directive (C/N) 95–246–

193(B), dated December 6, 1995, in

order to assure the continued

airworthiness of these airplanes in

France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of § 21.29 of

the Federal Aviation Regulations (14

CFR 21.29) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

modifying the rudder trim switch and

control knob. The actions would be

required to be accomplished in

accordance with the service bulletins

described previously.

Cost Impact

The FAA estimates that 85 Airbus

Industrie Model A310 and A300–600

series airplanes of U.S. registry would

be affected by this proposed AD, that it

would take approximately 7 work hours

per airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $789 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $102,765, or

$1,209 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 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

adding the following new airworthiness

directive:

Airbus Industrie: Docket 96–NM–194–AD.

Applicability: Model A310 and A300–600

series airplanes, on which Airbus Industrie

Modifications 8566 and 10866 have not been

incorporated; certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability
Federal Register / Vol. 62, No. 62 / Tuesday, April 1, 1997 / Proposed Rules 15433

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 (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 uncommanded activation of the

rudder trim, which, if not corrected, could

lead to uncommanded yaw/roll excursions

and consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 90 days after the effective date

of this AD, replace the rudder trim switch,

control knob, and associated wires with new

components and wiring in accordance with

the applicable Airbus Industrie service

bulletin specified in paragraph (a)(1) or (a)(2)

of this AD.

(1) For Model A300–600 series airplanes:

Airbus Service Bulletins A300–27–6022,

Revision 2, dated August 28, 1995; and

A300–27–6027, Revision 2, dated August 22,

1995, or Revision 3, dated March 13, 1996.

(2) For Model A310 series airplanes:

Airbus Service Bulletins A310–27–2058,

Revision 2, dated August 28, 1995; and

A310–27–2071, Revision 2, dated August 22,

1995, or Revision 3, dated March 13, 1996.

Note 2: Modifications accomplished prior

to the effective date of this AD in accordance

with Airbus Service Bulletin A300–27–6027,

Revision 2, dated August 22, 1995 (for Model

A300–600 series airplanes), or A310–27–

2071, Revision 2, dated August 22, 1995 (for

Model A310 series airplanes), are considered

acceptable for compliance with the

applicable action specified in this AD.

(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,

Standardization Branch, ANM–113, 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, Standardization

Branch, ANM–113.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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.

Issued in Renton, Washington, on March

25, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–8126 Filed 3–31–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–171–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400, –400D, and –400F

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 Boeing Model 747–400, –400D,

and –400F series airplanes. This

proposal would require modification of

the P212 and P213 panels of the cabin

pressure control system. This proposal

is prompted by a report of in-flight loss

of cabin pressurization control due to a

single failure of the auxiliary power unit

(APU) battery. The actions specified by

the proposed AD are intended to

prevent loss of control of the cabin

pressurization system, which could

result in rapid depressurization of the

airplane. Such rapid depressurization

could result in deleterious physiological

effects on the passengers and crew; and

airplane diversions, which represent an

increased risk to the airplane,

passengers, and crew.

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–

171–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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Clayton R. Morris, Jr., Aerospace

Engineer, Systems and Equipment

Branch, ANM–130S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington;

telephone (206) 227–2794; fax (206)

227–1181.

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–171–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–171–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA received a report indicating

that power from the 28-volt direct

current (DC) hot battery bus of the

auxiliary power unit (APU) was lost

during flight on a Model 747–400 series

airplane. Loss of power from the hot

battery bus resulted in loss of a discrete

signal to both interface control units

(ICU’s). Loss of the discrete signal

indicated that ‘‘manual’’ control mode

was selected, but the cabin pressure

control system was still in ‘‘automatic’’

control mode. The ICU’s went into

standby mode and transmitted this

status to both cabin pressure controllers

(CPC’s). The CPC’s then went into