Federal Register / Vol. 62, No. 26 / Friday, February 7, 1997 / Proposed Rules 5783

Please notify Sandy Beall at the above

address of your intention to attend the

workshop or if you have written

comments.

Issued in Washington, DC on January 31,

1997.

Christine A. Ervin,

Assistant Secretary, Energy Efficiency and

Renewable Energy.

[FR Doc. 97–3063 Filed 2–6–97; 8:45 am]

BILLING CODE 6450–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–260–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–100, –200, –300, and –400

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 747–100, –200,

–300, and –400 series airplanes. This

proposal would require a one-time

visual inspection to determine the part

number of the fuel shutoff valve

installed in the outboard engines. The

proposed AD also would require

replacement of certain valves with new

valves, or modification of the spar valve

body assembly, and various follow-on

actions. This proposal is prompted by

reports indicating that, due to high fuel

pressure, certain fuel system

components of the outboard engines

have failed on in-service airplanes. The

actions specified by the proposed AD

are intended to prevent such high fuel

pressure, which could result in failure

of the fuel system components; this

situation could result in fuel leakage

and, consequently, lead to an engine

fire.

DATES: Comments must be received by

March 20, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

260–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; or ITT Aerospace Controls,

28150 Industry Drive, Valencia,

California 91355. This information may

be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Sulmo Mariano, Aerospace Engineer,

Propulsion Branch, ANM–140S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington; telephone (206) 227–2686;

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–260–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–260–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received several reports

indicating that, due to high fuel

pressure, the fuel system components of

the outboard engines have failed on

Boeing Model 747 series airplanes:

1. Four incidents on airplanes

powered by General Electric engines in

which the fuel pump inlet of the engine

was found to be cracked.

2. Two incidents on airplanes

powered by Rolls Royce engines, in

which the low pressure fuel filter

housing on the engine was found to be

cracked.

3. Two incidents on airplanes

powered by Rolls Royce engines, in

which the fuel cooled oil cooler on the

engine was found to be ruptured.

The existing design of the fuel shutoff

spar valve installed on certain Model

747 series airplanes powered by General

Electric and Rolls Royce engines can

cause high pressure to occur in the fuel

line. High fuel pressure can occur after

the fuel shutoff spar valve and the

engine fuel shutoff valve are closed

during engine shutdown. This can result

in heating of the trapped fuel and,

because these valves are closed, the

pressure created from the heating

process is not released.

High fuel pressure could result in

failure of the fuel system components. If

any of these components fails, the

resultant fuel leakage could result in a

possible engine fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

28A2199, dated August 1, 1996. The

alert service bulletin describes

procedures for performing a visual

inspection to determine the part number

of the fuel shutoff valve installed in the

left and right-hand outboard engines;

and replacement of certain valves with

new valves and various follow-on

actions, if necessary. [These follow-on

actions include aligning valve(s),

performing a check to detect leaks, and

correcting any discrepancy.] The new

fuel shutoff valve will ensure that the

fuel pressure is released at 55–70

pounds per square inch gauge (p.s.i.g.).

The FAA has also reviewed and

approved ITT Service Bulletins

SB125120–28–01, SB107970–28–01,

and SB125334–28–01; all dated July 15,

1996. These service bulletins describe

procedures for modification of the spar

valve body assembly. The modifications

involve replacement of the thermal

relief valves located in the valve disc

with new thermal relief valves. Back

pressure on the thermal relief valve can

cause the valves to open at a higher

pressure than desired. Accomplishment

of these modifications will reduce the

opening pressure of the thermal relief

valves.
5784 Federal Register / Vol. 62, No. 26 / Friday, February 7, 1997 / Proposed Rules

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

require a one-time visual inspection to

verify if the proper fuel shutoff valve is

installed in the left and right-hand

outboard engines. The proposed AD also

would require replacement of any

improper valve with a new valve or

modification of the spar valve body

assembly, and various follow-on

actions. The actions would be required

to be accomplished in accordance with

the service bulletins described

previously.

The FAA also has determined that,

following accomplishment of the

proposed visual inspection and

replacement or modifications, a onetime inspection to detect fuel leaks of

the components between the fuel

shutoff spar valve and the engine fuel

shutoff valve to ascertain the integrity of

these components is necessary. This

proposed AD would require that this

one-time inspection for leakage be

accomplished and that any discrepant

part be replaced with a serviceable part.

These actions would be required to be

accomplished in accordance with the

applicable section that pertains to Rolls

Royce RB211 series engines or General

Electric CF6–80C and CF6–45/50 series

engines in Chapter 71 of the Boeing 747

Airplane Maintenance Manual (AMM).

Cost Impact

There are approximately 418 Boeing

Model 747–100, –200, –300, and –400

series airplanes of the affected design in

the worldwide fleet. The FAA estimates

that 24 airplanes of U.S. registry would

be affected by this proposed AD.

It would take approximately 4 work

hours per airplane to accomplish the

proposed one-time visual inspection to

determine the part number of the valve,

at an average labor rate of $60 per work

hour. Based on these figures, the cost

impact of the visual proposed by this

AD on U.S. operators is estimated to be

$5,760, or $240 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.

Should an operator elect to modify

the valve body assembly of the fuel

system rather than replace a discrepant

valve, it would take approximately 20

work hours per airplane, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $404 (2 kits) per

airplane. Based on these figures, the cost

impact of any necessary modification

action is estimated to be $1,604 per

airplane.

Should an operator be required to

accomplish the necessary one-time

inspection to detect leaks and cracks

(after replacement of the valve or

modification of the assembly), it would

take approximately 16 work hours per

airplane, at an average labor rate of $60

per work hour. Based on these figures,

the cost impact of this one-time

inspection is estimated to be $960 per

airplane.

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:

Boeing: Docket 96–NM–260–AD.

Applicability: Model 747–100, –200, –300,

and –400 series airplanes, having line

numbers 001 through 1006, inclusive, and

powered by General Electric or Rolls Royce

engines; 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 high fuel pressure in

components between the fuel shutoff spar

valve and the engine fuel shutoff valve,

which could result in failure of the fuel

system components, lead to fuel leakage, and,

consequently, lead to a possible engine fire,

accomplish the following:

(a) Within 12 months after the effective

date of this AD, perform a one-time visual

inspection to determine the part number of

the fuel shutoff valve installed in the leftand right-hand outboard engines, in

accordance with Boeing Alert Service

Bulletin 747–28A2199, dated August 1, 1996.

(1) If a valve having P/N S343T003–40 (ITT

P/N 125334D–1) is installed, no further

action is required by this AD.

(2) If a valve having P/N S343T003–40 (ITT

P/N 125334D–1) is not installed, prior to

further flight, accomplish either paragraph

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

(i) Replace the valve with a new valve, in

accordance with the alert service bulletin.

Prior to further flight following

accomplishment of the replacement, align the

valve(s), perform a check to detect leaks, and

correct any discrepancy, in accordance with

the alert service bulletin. Or

(ii) Modify the valve body assembly of the

fuel system in accordance with ITT Service

Bulletin SB125120–28–01, ITT Service

Bulletin SB107970–28–01, and ITT Service

Bulletin SB125334–28–01; all dated July 15,

1996.

(b) Prior to further flight following

accomplishment of paragraph (a)(2) of this

AD, perform a one-time inspection to detect

fuel leaks of the components between the

fuel shutoff spar valve and the engine fuel

shutoff valve on all four engines, in

accordance with the applicable section that

pertains to Rolls Royce RB211 series engines

or General Electric CF6–80C and CF6–45/50

series engines in Chapter 71 of the Boeing

747 Airplane Maintenance Manual (AMM). If
Federal Register / Vol. 62, No. 26 / Friday, February 7, 1997 / Proposed Rules 5785

any leak is detected, prior to further flight,

replace the part with a serviceable part.

(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, Seattle

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, Seattle ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle 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 January

31, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3029 Filed 2–6–97; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 96–NM–137–AD]

RIN 2120–AA64

Airworthiness Directives;

Construcciones Aeronauticas, S.A.

(CASA) Model CN–235 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 CASA Model CN–235 series

airplanes. This proposal would require

repetitive inspections of the torsion

tubes and fittings of the elevator and

rudder assemblies to detect stress

corrosion cracking, and replacement of

cracked parts. This proposed action also

would require the accomplishment of a

modification that would constitute

terminating action for the repetitive

inspections. This proposal is prompted

by reports indicating that stress

corrosion cracking in these parts has

been found on some airplanes. The

actions specified by the proposed AD

are intended to prevent loss of control

of the elevator and/or rudder, due to

failure of the elevator and/or rudder

assemblies as a result of stress corrosion

cracking.

DATES: Comments must be received by

March 20, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

137–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

Construcciones Aeronauticas, S.A.,

Getafe, Madrid, Spain. This information

may be examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Greg

Dunn, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2799; 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

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–137–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–137–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direccio ́n General de Aviacio ́n

(DGAC), which is the airworthiness

authority for Spain, has notified the

FAA that an unsafe condition may exist

on certain CASA Model CN–235 series

airplanes. The DGAC advises that it has

received reports indicating that stress

corrosion cracks were detected in the

torsion tubes and fittings of the elevator

and rudder assemblies on some of these

airplanes. This condition, if not

corrected, could result in failure of these

assemblies and subsequent loss of

control of the elevator and/or rudder.

Explanation of Relevant Service

Information

CASA has issued Service Bulletin SB–

235–27–05, Revision 1, dated September

29, 1993 (for non-military airplanes),

and Service Bulletin SB–235–27–05M,

Revision 2, dated January 25, 1996 (for

military airplanes). These service

bulletins describe procedures for

conducting repetitive visual inspections

of the torsion tubes for the rudder and

elevator to detect stress corrosion

cracking, and replacement of discrepant

tubes with tubes of a new design.

Installation of the newly-designed

torsion tubes is intended to preclude

stress corrosion cracking and eliminates

the need for repetitive visual

inspections.

The DGAC classified Service Bulletin

SB–235–27–05 (for non-military

airplanes) as mandatory and issued

Spanish airworthiness directive 06/94,

dated August 1994, in order to assure

the continued airworthiness of these

airplanes in Spain. The DGAC classified

Service Bulletin SB–235–27–05M (for

military airplanes) as ‘‘recommended.’’

FAA’s Conclusions

This airplane model is manufactured

in Spain and is type certificated for

operation in the United States under the

provisions of section 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.