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
Federal Register / Vol. 63, No. 126 /Wednesday, July 1, 1998 /Rules and Regulations 35797

Engineer, FAA, Wichita Aircraft

Certification Office, 1801 Airport Road,

RM 100, Mid-Continent Airport,

Wichita, Kansas, 67209, telephone:

(316) 946–4128; facsimile: (316) 946–

4407.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Cessna Model 172R

airplanes was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on February 13,

1998 (63 FR 7322). The NPRM proposed

to require modifying the lower forward

doorpost bulkhead on both sides of the

affected model airplanes by installing

rivets. Accomplishment of the proposed

action as specified in the NPRM would

be in accordance with Cessna Service

Bulletin No. SB97–53–02, dated

September 15, 1997.

The NPRM was the result of a report

from the manufacturer that these rivets

were erroneously omitted during

manufacture of some of the new

production airplanes.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 87 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

14 workhours per airplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $150

per airplane. Based on these figures, the

total cost impact of this AD on U.S.

operators is estimated to be $86,130, or

$990 per airplane. The FAA assumes

that none of the owners/operators of the

affected airplanes have accomplished

this action.

Regulatory Impact

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 copy of the final

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, 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 a new airworthiness directive

(AD) to read as follows:

98–14–07 Cessna Aircraft Company:

Amendment 39–10641; Docket No. 97–

CE–96–AD.

Applicability: Model 172R airplanes with

the following serial numbers, certificated in

any category: 17280004 through 17280016,

17280018 through 17280050, 17280052

through 17280058, 17280060 through

17280062, 17280064, 17280066 through

17280082, 17280085 through 17280099,

17280101 through 17280113, 17280115,

17280116, 17280118 through 17280125,

17280128 through 17280131, and 17280138.

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 within the next 100

hours time-in-service (TIS) after the effective

date of this AD, unless already accomplished.

To prevent reduced structural rigidity at

the lower forward doorpost bulkhead, which

could result in structural cracking and

possible loss of control of the airplane,

accomplish the following:

(a) Modify the lower forward doorpost of

the affected airplanes by installing the

specified rivets in accordance with Cessna

Service Bulletin No. SB97–53–02, dated

September 15, 1997.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Rm. 100, Mid-Continent Airport,

Wichita, Kansas, 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(d) The modification required by this AD

shall be done in accordance with Cessna

Service Bulletin No. SB97–53–02, dated

September 15, 1997. 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 The Cessna Aircraft Company,

P. O. Box 7706, Wichita, Kansas 67277.

Copies may be inspected at the FAA, Central

Region, Office of the Regional Counsel, Room

1558, 601 E. 12th Street, Kansas City,

Missouri, or at the Office of the Federal

Register, 800 North Capitol Street, NW, suite

700, Washington, DC.

(e) This amendment becomes effective on

August 16, 1998.

Issued in Kansas City, Missouri, on June

24, 1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–17414 Filed 6–30–98; 8:45 am]

BILLING CODE 4910–13–U