35794 Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations

responsibilities among the various

levels of government. Therefore, in

accordance with Executive Order 12612,

it is determined that this final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–14–06 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10640. Docket 98–NM–113–AD.

Applicability: BAe Model ATP airplanes,

as listed in British Aerospace Alert Service

Bulletin ATP–32–85, Revision 1, dated

March 20, 1998; certificated in any category.

Note 1: This AD applies to each airplane

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

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 failure of the spring strut

assembly of the forward door of the main

landing gear (MLG), which could result in

the inability to extend the MLG, accomplish

the following:

(a) Within 600 flight hours after the

effective date of this AD, perform a visual

inspection for discrepancies of the fork end

of the spring strut assembly of the forward

door of the MLG, on the left and right sides

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 sides 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.

(e) The replacement shall be done in

accordance with British Aerospace Service

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

The inspection shall be done in accordance

with British Aerospace Alert Service Bulletin

ATP–32–85, Revision 1, dated March 20,

1998, which contains the following effective

pages:

Page No. shown on

page

Revision

level

shown on

page

Date

shown on

page

1–3, 6, 7, 10 ............. 1 ............. March 20,

1998.

4, 5, 8, 9, 11 ............. Original .. January

26,

1998.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from AI(R) American Support, Inc., 13850

Mclearen Road, Herndon, Virginia 20171.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

(f) This amendment becomes effective on

August 5, 1998.

Issued in Renton, Washington, on June 24,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17417 Filed 6–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–33–AD; Amendment

39–10636; AD 98–14–02]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney Canada PW100 Series

Turboprop Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Pratt & Whitney Canada

(PWC) PW100 series turboprop engines,

that requires removal of the existing fuel

manifold tubes, lock plates, and

preformed packing; installation of

improved fuel manifold transfer tubes,

improved lock plates, and improved

preformed packing; and, after

installation, the performance of a leak

check. This amendment is prompted by

reports of engine fuel leaks which

resulted in either inflight engine

shutdowns or fire warnings. The actions

specified by this AD are intended to

prevent engine fuel leaks, which can

result in inflight engine shutdowns or

fire warnings.

DATES: Effective August 31, 1998.
Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations 35795

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 31,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Pratt & Whitney Canada, 1000

Marie-Victorin, Longueuil, Quebec,

Canada J4G 1A1; telephone (514) 677–

9411, fax (514) 647–3620. This

information may be examined at the

Federal Aviation Administration (FAA),

New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Jason Yang, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7747, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Pratt & Whitney

Canada (PWC) PW118, PW118A,

PW118B, PW119B, PW119C, PW120,

PW120A, PW121, PW121A, PW123,

PW123B, PW123C, PW123D, PW123E,

PW124B, PW125B, PW126A, PW127,

PW127E, PW127F series turboprop

engines was published in the Federal

Register on October 24, 1997 (62 FR

55364). That action proposed to require

removal of the existing fuel manifold

tubes, lock plates, and preformed

packing and installation of improved

fuel manifold transfer tubes, lock plates,

and preformed packing, at the earliest of

the following: (1) the next time, after the

effective date of this AD, that the engine

or module is at a maintenance base that

can do the modifications specified,

regardless of the scheduled maintenance

action or reason for engine removal; (2)

or at the next fuel nozzle change; or (3)

prior to November 30, 1998. This

calendar end-date was determined

based upon risk assessment. After

installation, but prior to further flight,

this AD requires performing a leak

check.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

One commenter states that the

affected part numbers (P/Ns) are not

identified in the proposed rule. The

FAA does not concur. The affected P/Ns

have been referenced in the applicable

PWC Service Bulletins (SBs).

One commenter states that the parts to

be installed should not be limited to the

part numbers identified in the existing

SBs. The AD should make allowance for

installing new parts identified in

subsequent revisions. The FAA does not

concur. The FAA cannot approve

nonexistent parts of future designs,

hence the reference of subsequent

revision of SB in the AD is not

permitted. However, additional parts

may be introduced by an AD revision,

or through alternative methods of

compliance requests.

One commenter states that the

requirements of PWC SB No. 21549 are

not necessary and should not be

required by the proposed rule. The FAA

does not concur. That SB introduced

improved drain tubes, that have been

shown to reduce or prevent fires. Drain

tube leaks have been attributed to

several inflight engine fires.

One commenter states that the drain

tubes should be installed in accordance

with PWC SB No. 21077. The FAA

concurs in part with the comment that

PWC SB No. 21077 provides

instructions for the part removal and

replacement. However, the installation

of fuel manifold drain tubes may be

accomplished in accordance with PWC

SB No. 21549 or PWC SB No. 21077. In

addition, fuel manifold transfer tube

installed in accordance with PWC No.

21077 or PWC SB No. 21516 is also

acceptable. Paragraph (a) of the AD

compliance section has been modified

accordingly.

Since publication of the NPRM, the

manufacturer has issued PWC SB No.

21077, Revision 8, dated April 4, 1998.

This final rule references this latest

revision.

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

The FAA estimates that 1,216 engines

installed on aircraft of U.S. registry will

be affected by this AD, that it will not

take any additional work hours per

engine to accomplish the proposed

actions, as the actions may be performed

during regularly scheduled maintenance

or overhaul. Required parts will cost

approximately $370 per engine. Based

on these figures, the total cost impact of

the AD on U.S. operators is estimated to

be $449,920.

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

For the reasons discussed above, I

certify that this action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under DOT

Regulatory Policies and Procedures (44

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

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–14–02 Pratt & Whitney Canada:

Amendment 39–10636. Docket 97–ANE–

33–AD.

Applicability: Pratt & Whitney Canada

(PWC) PW118, W118A, PW118B, PW119B,

PW119C, PW120, PW120A, PW121, W121A,

PW123, PW123B, PW123C, PW123D,

PW123E, PW124B, PW125B, PW126A,

PW127, PW127E, PW127F series engines

installed on but not limited to Dornier 328,

Fokker 50, Jetstream ATP, ATR42, ATR42–

500, ATR72, Embraer EMB–120, Canadair

CL215T, CL415, and DeHavilland Dash-8–

100/–200/–300/–315.

Note 1: This airworthiness directive (AD)

applies to each engine identified in the
35796 Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations

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 (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 engine fuel leaks, which can

result in inflight engine shutdowns or fire

warnings, accomplish the following:

(a) Remove the existing fuel manifold

transfer tubes, transfer tube lock plates, and

fuel manifold drain tubes in accordance with

PWC Service Bulletin (SB) No. 21077,

Revision 8, dated April 4, 1998. Remove the

existing preformed packing in accordance

with PWC SB No. 21364, Revision 1, dated

April 28, 1995. Replace with fuel manifold

transfer tubes in accordance with the

following applicable PWC Service Bulletins

(SBs): No. 21077, Revision 8, dated April 4,

1998, or No. 21516, dated August 14, 1997.

Replace fuel manifold drain tubes in

accordance with PWC SB No. 21549, dated

September 18, 1997 or SB No. 21077,

Revision 8, dated April 4, 1998. The

modification must include installation of the

improved lock plates in accordance with

PWC SB No. 21373, Revision 3, dated

October 11, 1996, and the preformed packing

in accordance with PWC SB No. 21364,

Revision 1, dated April 28, 1995, as follows,

whichever occurs first following the effective

date of this AD:

(1) At the next engine removal, regardless

of cause; or

(2) At the next fuel nozzle change; or

(3) Prior to November 30, 1998.

(b) After the installation of the improved

fuel manifold tubes and lockplates, but prior

to further flight, perform a leak check in

accordance with the applicable maintenance

manual.

(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, 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.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

(e) The actions required by this AD shall

be done in accordance with the following

PWC SBs:

Document No Pages Revision Date

21077 .............................................................................................................................................................. 1–9 8 ............. April 4, 1998.

Total Pages: 9

21516 .............................................................................................................................................................. 1–5 Original .. August 14,

1997.

Total Pages: 5.

21549 .............................................................................................................................................................. 1–4 Original .. September 18,

1997.

Total Pages: 4.

21373 .............................................................................................................................................................. 1–11 3 ............. October 11,

1996.

Total Pages: 11.

21364 .............................................................................................................................................................. 1–8 1 ............. April 28, 1995.

Total Pages: 8.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Pratt & Whitney Canada, 1000 MarieVictorin, Longueuil, Quebec, Canada J4G

1A1; telephone (514) 677–9411, fax (514)

647–3620. Copies may be inspected at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England Executive

Park, Burlington, MA; or at the Office of the

Federal Register, 800 North Capitol Street

NW., suite 700, Washington, DC.

(f) This amendment becomes effective on

August 31, 1998.

Issued in Burlington, Massachusetts, on

June 23, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–17415 Filed 6–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–96–AD; Amendment 39–

10641; AD 98–14–07]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Model 172R

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Cessna Aircraft

Company Model 172R airplanes. This

AD requires modifying the lower

forward doorpost bulkhead by installing

rivets. This AD is the result of a report

from the manufacturer that these rivets

were erroneously omitted during

manufacture of some of the new

production airplanes. The actions

specified by this AD are intended to

prevent reduced structural rigidity at

the forward doorpost bulkhead, which

could result in structural cracking and

possible loss of control of the airplane.

DATES: Effective August 16, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 16,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

The Cessna Aircraft Company, P. O. Box

7706, Wichita, Kansas 67277, telephone:

(316) 941–7550, facsimile: (316) 942–

9008. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–96–

AD, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Eual Conditt, Senior Aerospace