24138 Federal Register / Vol. 63, No. 84 / Friday, May 1, 1998 / Proposed Rules

inspection for discrepancies of the fork end

of the spring strut assembly of the forward

door of the MLG, on the left and right side

of the airplane; in accordance with British

Aerospace Alert Service Bulletin ATP–32–85,

Revision 1, dated March 20, 1998.

(1) If no discrepancy is detected, repeat the

visual inspection thereafter at intervals not to

exceed 1,500 flight hours until the actions

specified by paragraph (b) of this AD are

accomplished.

(2) If any discrepancy is detected, prior to

further flight, replace the existing spring strut

assembly with a new or serviceable part, in

accordance with the alert service bulletin.

Repeat the visual inspection thereafter at

intervals not to exceed 1,500 flight hours

until the actions specified by paragraph (b)

of this AD are accomplished.

(b) Within 18 months after the effective

date of this AD, replace the spring strut

assembly of the forward door of the MLG

with an improved spring strut assembly, on

the left and right side of the airplane; in

accordance with British Aerospace Service

Bulletin ATP–32–87, dated January 29, 1998.

This replacement constitutes terminating

action for the requirements 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,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their request through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 April 24,

1998.

Gary L. Killion,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11561 Filed 4–30–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–59–AD]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney JT8D Series Turbofan Engines

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 certain

Pratt & Whitney (PW) JT8D series

turbofan engines, that currently requires

initial and repetitive inspections of the

No. 7 fuel nozzle and support assembly,

replacement of the No. 7 fuel nozzle and

support assembly with a more leakresistant configuration, and replacement

of aluminum oil pressure and scavenge

tube fittings with steel fittings. In

addition, the current AD requires

replacing an additional aluminum oil

scavenge line bolt with a steel bolt. This

action would require initial and

repetitive borescope inspections for loss

of fuel nozzle nut torque and nozzle

support wear, and replacement or

modification of the fuel nozzles at the

next accessibility of the diffuser build

group as terminating action to the

inspections. This proposal is prompted

by reports of loss of fuel nozzle nut

torque and nozzle support wear. The

actions specified by the proposed AD

are intended to prevent loss of fuel

nozzle nut torque and nozzle support

wear, which could result in a fuel leak

and possible engine fire.

DATES: Comments must be received by

June 30, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

59–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays. The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, 400 Main St., East

Hartford, CT 06108; telephone (860)

565–6600, fax (860) 565–4503. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Christopher Spinney, Aerospace

Engineer, Engine Certification Office,

FAA, Engine and Propeller Directorate,

telephone (781) 238–7175, fax (781)

238–7199.

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

should 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–ANE–59–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–ANE–59–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

On January 24, 1995, the Federal

Aviation Administration (FAA) issued

airworthiness directive AD 95–02–16,

Amendment 39–9135 (60 FR 6654,

February 3, 1995), applicable to Pratt &

Whitney (PW) JT8D series turbofan

engines, to require inspection of the No.

7 fuel nozzle and support assembly for

evidence of fuel leakage and burning

until replacement of the No. 7 fuel

nozzle and support assembly with an

improved sealing configuration. That

AD also requires replacement of the

aluminum oil tube fittings with steel

fittings. In addition, that AD requires

replacing an additional aluminum oil

scavenge line bolt with a steel bolt. That

action was prompted by reports of two

uncontained engine fires due to fuel

leakage from the No. 7 fuel nozzle and
Federal Register / Vol. 63, No. 84 / Friday, May 1, 1998 / Proposed Rules 24139

support assembly, ignition of that fuel,

melting of aluminum oil pressure and

scavenge tube fittings that are in the

proximity of the No. 7 nozzle, and

augmentation of that fire with the

liberated oil. That condition, if not

corrected, could result in fuel leakage

from the No. 7 fuel nozzle and support

assembly, ignition of that leaking fuel,

and liberation of oil from melted oil line

fittings, which can result in an

uncontained engine fire and damage to

the aircraft.

Since the issuance of that AD, the

FAA has received reports of loss of fuel

nozzle nut torque and nozzle support

wear. AD 95–02–16 mandated welding

of the No. 7 fuel nozzles to the fuel

nozzle support to prevent secondary

fuel leakage and replacement of oil

scavenge lines to a more fire resistant

stainless steel. Field experience has

shown that the welding of the fuel

nozzle to the fuel nozzle support can

cause a loss of torque on the fuel nozzle

nut. The loss of torque on the fuel

nozzle nut results in rotation of the nut

and air scoop assembly and subsequent

contact between the airscoop and the

nozzle support fairing, resulting in wear

through the fairing and nozzle support

and eventually a secondary fuel leak.

The loss of nut torque has also been

reported to cause thread wear, which in

some cases has resulted in liberation of

the nozzle from the support after it has

been removed from the engine.

The FAA has reviewed and approved

the technical contents of PW Alert

Service Bulletin (ASB) No. A6310, dated

October 13, 1997, that describes

procedures for inspections for loss of

fuel nozzle nut torque and nozzle

support wear, and ASB No. A6311,

dated October 14, 1997, that describes

procedures for replacement or

modification of fuel nozzles to an

improved design.

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 95–02–16 to require

initial and repetitive inspections for loss

of fuel nozzle nut torque and nozzle

support wear, and replacement or

modification of the fuel nozzles at the

next accessibility of the diffuser build

group as terminating action to the

inspections. The calendar end-date was

determined based upon risk analysis

and parts availability.

There are approximately 13,902

engines of the affected design in the

worldwide fleet. The FAA estimates that

7,100 engines installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 0.3 work hours per

engine to accomplish the proposed

inspections, and 9.2 hours to perform

the proposed modifications or

replacement, and that the average labor

rate is $60 per work hour. Required

parts would cost approximately $12,620

per engine to replace the nozzle and

$1,500 to modify existing nozzles. The

FAA estimates that 10% of the nozzles

will have to be replaced. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $18,950,000 .

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 9135 (60 FR 6654,

February 3, 1995) and by adding a new

airworthiness directive to read as

follows:

Pratt & Whitney: Docket No. 97–ANE–59–

AD. Supersedes AD 95–02–16,

Amendment 39–9135.

Applicability: Pratt & Whitney (PW) Model

JT8D–209, –217, –217A, –217C, –219, –1,

–1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15,

–15A, –17, –17A, –17R, and –17AR turbofan

engines incorporating the modifications

described in PW Service Bulletin (SB) No.

5650, dated January 17, 1986, Alert Service

Bulletin (ASB) No. A6169, Revision 4, dated

June 5, 1996, or earlier revisions, or SB 6240,

dated January 20, 1996, and any PW Model

JT8D engine with low emissions fuel nozzle

and support assemblies, Part Numbers

775485, 809137–01, 802965, 5004308–02,

5004308–032, 814358, 5004308–042 or

815658–01 installed. These engines are

installed on but not limited to Boeing 727

and 737 series, and McDonnell Douglas DC–

9 and MD–80 series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 (f)

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 loss of fuel nozzle nut torque

and nozzle support wear, which could result

in a fuel leak and possible engine fire,

accomplish the following:

(a) For engines that have not incorporated

modifications to the No. 7 fuel nozzle and

support assembly in accordance with PW

ASB No. A6169, Revision 4, dated January

20, 1996, or earlier revisions, or PW SB No.

6240, dated January 20, 1996, as of the

effective date of this AD; or for engines that

have not incorporated the oil scavenge tube

and fitting modifications in accordance with

ASB No. A6170, dated October 20, 1994, as

of the effective date of this AD, accomplish

the following:

(1) Inspect No. 7 fuel nozzle and support

assemblies in accordance with PW ASB No.

A6153, Revision 1, dated June 8, 1994, as

follows:

(i) For engines that have accumulated

3,200 hours or more time in service (TIS)

since last fuel nozzle and support assembly

overhaul and have not received an initial

inspection for fuel leakage, perform an initial

inspection for fuel leakage before further

flight.

(ii) For engines that have accumulated less

than 3,200 hours TIS since last fuel nozzle

and support assembly overhaul and have not

received an initial inspection for fuel leakage,

perform an initial inspection for fuel leakage
24140 Federal Register / Vol. 63, No. 84 / Friday, May 1, 1998 / Proposed Rules

prior to accumulating 3,200 hours TIS since

last fuel nozzle and support assembly

overhaul.

(iii) Thereafter, inspect for fuel leakage in

accordance with PW ASB A6153, Revision 1,

dated June 8, 1994, at intervals not to exceed

700 hours TIS since last inspection.

(iv) Remove from service No. 7 fuel nozzle

and support assemblies that exhibit evidence

of fuel leakage as described in PW ASB No.

A6153, Revision 1, dated June 8, 1994, and

replace with the improved sealing

configuration nozzle in accordance with

paragraph (a)(2)(i) of this AD, as follows:

(A) Within 25 hours TIS, or 25 cycles in

service (CIS), whichever occurs first, after the

inspection performed in paragraph (a)(1) for

aircraft with only one engine exhibiting No.

7 fuel nozzle and support assembly leakage.

(B) Prior to further flight, on aircraft with

two or more engines exhibiting No. 7 fuel

nozzle and support assembly leakage, remove

and replace at least all but one of the leaking

No. 7 fuel nozzle and support assemblies. If

not replacing all leaking No. 7 fuel nozzle

and support assemblies, the remaining No. 7

fuel nozzle and support assembly that

exhibits leakage shall be removed and

replaced in accordance with paragraph

(a)(1)(iv)(A) of this AD.

(2) At the next accessibility of the diffuser

build group after the effective date of the AD,

but no later than July 31, 1999, accomplish

the following:

(i) Replace the No. 7 fuel nozzle and

support assembly in accordance with

paragraph 1.B.(3) of the Accomplishment

Instructions of PW ASB No. A6311, dated

October 14, 1997.

(ii) Replace the aluminum pressure and

scavenge oil tube fittings with steel fittings in

accordance with PW ASB No. A6170,

Revision 2, dated October 20, 1994.

(iii) Replacement of the following oil tubes

with corresponding oil tubes that incorporate

steel fittings constitutes compliance with

paragraph (b)(2) of this AD:

(A) Outer internal No. 4 and 5 bearing

pressure tube assembly for PW JT8D–200

series engines.

(B) Outer internal main bearing pressure

tube assembly for PW JT8D–200 series

engines.

(C) Main bearing pressure manifold

assembly for PW JT8D–200 series engines.

(D) Front No. 4 1/2 and 6 bearing pressure

tube assembly for JT8D–200 series engines.

(E) No. 4 bearing oil scavenge tube

assembly for all other JT8D engines.

(F) No. 4 bearing oil pressure tube

assembly for all other JT8D engines.

(G) Main bearing pressure manifold

assembly for all other JT8D engines.

(3) Incorporation of the hardware required

by paragraph (a)(2)(i) of this AD constitutes

terminating action for the inspections

required by paragraphs (a)(1) of this AD.

(b) For engines that have incorporated

modifications of the No. 7 fuel nozzle and

support assembly in accordance with PW

ASB No. A6169, Revision 4, dated June 5,

1996, or earlier revisions, and have not

incorporated the replacement of the No. 7

fuel nozzle and support assembly with a fuel

nozzle and support assembly with tack

welded lock tabs in accordance with PW SB

No. 6240, dated January 12, 1996, accomplish

the following.

(1) Borescope inspect, remove, and replace

fuel nozzle and support assemblies for nut

rotation in accordance with methods,

intervals and inspection criteria specified in

PW ASB No. 6310, dated October 13, 1997.

(2) At the next accessibility of the diffuser

build group after the effective date of the AD,

but no later than [Insert 5 years after the

effective date of the AD] , replace the No. 7

fuel nozzle and support assembly with a

welded air nozzle assembly in accordance

with paragraph 1.B.(1), 1.B.(2) and 1.B.(3) of

the Accomplishment Instructions of PW ASB

No. A6311, dated October 14, 1997.

(3) Accomplishment of paragraph (b)(2) of

this AD is terminating action to the

inspections of paragraph (b)(1) of this AD.

(c) For engines that have incorporated the

replacement of the No. 7 fuel nozzle and

support assembly with a fuel nozzle and

support assembly with tack welded lock tabs

in accordance with PW SB No. 6240, dated

January 12, 1996, at the next accessibility of

the diffuser build group after the effective

date of the AD, but no later than [insert 5

years after the effective date of the AD],

replace the No. 7 fuel nozzle and support

assembly with a welded air nozzle assembly

in accordance with paragraph 1.A.(1), 1.A.(2)

and 1.A.(3) of the Accomplishment

Instructions of PW ASB No. A6311, dated

October 14, 1997.

(d) For the purpose of this AD, accessibility

of the diffuser build group is defined as

engine maintenance that entails flange

separation of the diffuser case from the

combustion chamber outer case.

(e) For the purpose of this AD, fuel nozzle

and support assembly overhaul is defined as

disassembly of the fuel nozzle from the

support assembly that entails removal of the

fuel nozzle nut.

(f) 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, Engine

Certification Office. Operators shall submit

their requests through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(g) 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 aircraft to

a location where the requirements of this AD

can be accomplished.

Issued in Burlington, Massachusetts, on

April 23, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–11559 Filed 4–30–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–AWP–11]

Proposed Modification to Class E

Airspace; Ukiah, CA

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This notice proposes to

modify the Class E airspace at Ukiah,

CA, by lowering a portion of the base of

controlled airspace from 9,500 feet

mean sea level, (MSL) to 1,200 feet

above ground level (AGL). This action is

due to the proposed establishment of a

new federal airway (V–607) between

Mendocino and Arcata, CA. The

proposed airway, if adopted, will have

a minimum enroute altitude of 9,000

feet MSL. A review of airspace

classification has made this action

necessary in order to achieve

compliance with criteria stated in FAA

Order 7400.2D. The intended effect of

this proposal is to ensure that the Class

E airspace at Ukiah, CA will be of

sufficient size to contain V–607.

DATES: Comments must be received on

or before June 1, 1998.

ADDRESSES: Send comments on the

proposal in triplicate to: Federal

Aviation Administration, Attn:

Manager, Airspace Branch, AWP–520,

Docket No. 98–AWP–11, Air Traffic

Division, P.O. Box 92007, Worldway

Postal Center, Los Angeles, California

90009.

The official docket may be examined

in the Office of the Assistant Chief

Counsel, Western-Pacific Region,

Federal Aviation Administration, Room

6007, 15000 Aviation Boulevard,

Lawndale, California 90261.

An informal docket may also be

examined during normal business hours

at the Office of the Manager, Airspace

Branch, Air Traffic Division at the above

address.

FOR FURTHER INFORMATION CONTACT:

Larry Tonish, Airspace Specialist,

Airspace Branch, AWP–520, Air Traffic

Division, Western-Pacific Region,

Federal Aviation Administration, 15000

Aviation Boulevard, Lawndale, CA

90261, telephone (310) 725–6539.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested parties are invited to

participate in this proposed rulemaking

by submitting such written data, views,

or arguments, as they may desire.