60808 Federal Register / Vol. 62, No. 219 / Thursday, November 13, 1997 / Proposed Rules

and 4 passenger doors. The actions

would be required to be accomplished

in accordance with the service bulletin

described previously.

Cost Impact

There are approximately 673 Boeing

Model 757–200 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 381 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 6 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 $234 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $226,314, or

$594 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:

Boeing: Docket 96–NM–232–AD.

Applicability: Model 757–200 series

airplanes, as listed in Boeing Service Bulletin

757–25–0175, Revision 1, dated March 6,

1997, 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 inability to open the Number 1,

2, or 4 passenger door and to use the escape

slide at that door during an emergency

evacuation of the airplane, accomplish the

following:

(a) Within 18 months after the effective

date of this AD, modify the escape slide shelf

assemblies of the Numbers 1, 2, and 4

passenger doors in accordance with Boeing

Service Bulletin 757–25–0175, dated May 30,

1996, or Revision 1, dated March 6, 1997.

(b) As of the effective date of this AD, no

person shall install an escape slide shelf

assembly having part number 416N2400–6 or

416N2400–7 on any airplane.

(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

November 6, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29822 Filed 11–12–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–157–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–100, –200, –300, –400, and

–500 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

revise an existing airworthiness

directive (AD), applicable to all Boeing

Model 737–100, –200, –300, –400, and

–500 series airplanes, that currently

requires a one-time inspection to

determine the part number of the engage

solenoid valve of the yaw damper on the

rudder power control unit, and

replacement of the valve with a valve

having a different part number, if

necessary. That AD was prompted by a

review of the design of the flight control

systems on Model 737 series airplanes.

The actions specified by that AD are

intended to prevent sudden

uncommanded yawing of the airplane

due to potential failures within the yaw

damper system, and consequent injury

to passengers and crewmembers. This

action would make certain editorial

changes to clarify the requirements of

the existing AD.

DATES: Comments must be received by

December 29, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

157–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
Federal Register / Vol. 62, No. 219 / Thursday, November 13, 1997 / Proposed Rules 60809

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Tin

Truong, Aerospace Engineer, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2764; fax (425) 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 97–NM–157–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.

97–NM–157–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On April 24, 1997, the FAA issued

AD 97–09–15, amendment 39–10011 (62

FR 24325, May 5, 1997), applicable to

all Boeing Model 737–100, –200, –300,

–400, and –500 series airplanes, to

require a one-time inspection to

determine the part number of the engage

solenoid valve of the yaw damper, and

replacement of the valve with a valve

having a different part number, if

necessary. That action was prompted by

a review of the design of the flight

control systems on Model 737 series

airplanes. The requirements of that AD

are intended to prevent sudden

uncommanded yawing of the airplane

due to potential failures within the yaw

damper system, and consequent injury

to passengers and crewmembers.

Actions Since Issuance of Previous Rule

Since the issuance of AD 97–09–15,

the FAA has re-reviewed the

requirements of paragraph (a) and the

information specified in ‘‘Note 3’’ of

that AD.

The FAA finds that, as paragraph (a)

of AD 97–09–15 is currently worded,

operators could misinterpret exactly

which engage solenoid value of the yaw

damper must be inspected. Therefore,

the FAA has revised the phrase ‘‘engage

solenoid valve of the yaw damper’’ to

read ‘‘engage solenoid valve of the yaw

damper on the rudder power control

unit (PCU).’’

The FAA also finds that paragraph (a)

of AD 97–09–15 specifies only the

Boeing part number (P/N) for some

affected parts. For clarification

purposes, the FAA has revised

paragraph (a) of the existing AD to

include both the Boeing P/N and the

vendor P/N’s for all affected parts.

The FAA also has revised paragraph

(a) of the existing AD to reference

Chapter 22–11–61 (for Model 737–100

and –200 series airplanes) and Chapter

22–12–21 (for Model 737–300, –400,

and –500 series airplanes) of the Boeing

Maintenance Manual as the appropriate

sources of service information for

accomplishment of the actions required

by that paragraph.

Furthermore, the FAA finds that some

engage solenoid valves may be labeled

with only the name ‘‘Bertea,’’ rather

than ‘‘Parker’’ or ‘‘Parker-Bertea.’’

Therefore, the FAA has revised ‘‘Note

3’’ of AD 97–09–15 to include such

information regarding the labeling of the

engage solenoid valves.

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

revise AD 97–09–15 to continue to

require a one-time inspection to

determine the part number of the engage

solenoid valve of the yaw damper on the

rudder PCU, and replacement of the

valve with a valve having a different

part number, if necessary. The proposed

AD would make certain editorial

changes to clarify the requirements of

the existing AD.

Cost Impact

There are approximately 2,675 Boeing

Model 737 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 1,091 airplanes

of U.S. registry would be affected by this

proposed AD.

The FAA estimates that it would take

approximately 1 work hour per airplane

to accomplish the proposed one-time

inspection, at an average labor rate of

$60 per work hour. Based on these

figures, the cost impact of the inspection

proposed by this AD on U.S. operators

is estimated to be $65,460, or $60 per

airplane. The requirements of this AD

will add no new costs to affected

operators.

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
60810 Federal Register / Vol. 62, No. 219 / Thursday, November 13, 1997 / Proposed Rules

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 39–10011 (62 FR

24325, May 5, 1997), and by adding a

new airworthiness directive (AD), to

read as follows:

Boeing: Docket 97–NM–157–AD. Revises AD

97–09–15, Amendment 39–10011.

Applicability: All Model 737–100, –200,

–300, –400, and –500 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 (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 sudden uncommanded yawing

of the airplane due to potential failures

within the yaw damper system, and

consequent injury to passengers and

crewmembers, accomplish the following:

(a) Perform a one-time inspection of the

engage solenoid valve of the yaw damper on

the rudder power control unit (PCU) to

determine the part number (P/N) of the valve.

If any valve having Parker P/N 59600–5011

(Boeing P/N 10–60811–9), Parker P/N 59600–

5007 (Boeing P/N 10–60811–3), or Parker P/

N 59600–5003 (Boeing P/N 10–60811–1) is

installed, prior to further flight, replace it

with a valve having Parker P/N 881600–1001

(Boeing P/N 10–60811–13), Sterer P/N

45080–1 (Boeing P/N 10–60811–8), or Sterer

P/N 45080 (Boeing P/N 10–60811–3).

Accomplish the actions in accordance with

procedures specified in Chapter 22–11–61

(for Model 737–100 and –200 series

airplanes) or Chapter 22–12–21 (for Model

737–300, –400, and –500 series airplanes) of

the Boeing Maintenance Manual, as

applicable. Accomplish the inspection at the

earlier of the times specified in paragraphs

(a)(1) and (a)(2) of this AD.

(1) Within 5 years or 15,000 flight hours

after June 9, 1997 (the effective date of AD

97–09–15, amendment 39–10011), whichever

occurs first.

(2) At the next time the PCU is sent to a

repair facility.

Note 2: Boeing In-Service Activities Report

95–03–2725–10, dated February 16, 1995 (for

Model 737–100 and –200 series airplanes), or

95–04–2725–10, dated February 24, 1995 (for

Model 737–300, –400, and –500 series

airplanes), provides additional information

concerning interchangeability of solenoid

valve part numbers.

Note 3: Operators should note that, as

specified in paragraph (a) of this AD, both the

Parker and Sterer P/N’s have the same Boeing

P/N (10–60811–3). If, upon inspection,

Boeing P/N 10–60811–3 is found to be

installed, operators must ascertain the vendor

P/N. Parts having Boeing P/N 10–60811–3

and Parker P/N 59600–5007 must be replaced

and are not considered to be acceptable

replacement parts. In addition, some engage

solenoid valves may be labeled with only the

name ‘‘Bertea,’’ rather than ‘‘Parker’’ or

‘‘Parker-Bertea.’’

(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, 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 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(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

November 6, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–29820 Filed 11–12–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–238–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–100, –200, –300, –400, and

–500 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 all

Boeing Model 737–100, –200, –300,

–400, and –500 series airplanes. This

proposal would require installation of a

placard that warns the cabin crew not to

put the selector valve for the forward

lavatory water supply in the ‘‘DRAIN’’

position during flight. This proposal

also would require installation of an

isolation valve in the drain line

downstream of the selector valve. This

proposal is prompted by reports of

damage to the horizontal stabilizer and

engine flameout caused by ice formed

from water drained inadvertently

through a mispositioned selector valve.

The actions specified by the proposed

AD are intended to prevent damage to

the engines, airframe, or horizontal

stabilizer, and/or prevent a hazard to

persons or property on the ground, as a

result of ice that could dislodge from the

airplane.

DATES: Comments must be received by

December 29, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

238–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.

FOR FURTHER INFORMATION CONTACT: Don

Eiford, Aerospace Engineer, Systems

and Equipment Branch, ANM–130S,

FAA, Transport Airplane Directorate,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2788; fax (425) 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