Federal Register / Vol. 63, No. 116 /Wednesday, June 17, 1998 /Rules and Regulations 32973

in addition, portions of Amendments

29–12, specifically, §§ 29.67, 29.71,

29.75, 29.141, 29.173, 29.175, 29.931,

29.1189(a)(2), 29.1555(c)(2), 29 1557(c),

and portions of Amendment 29–13,

specifically § 29.965, and Amendment

29–21. In addition, for the Sikorsky

Model S76C (with Arriel 2S1 Engine

Configuration): Amendment 29–34

specifically 29.67(a)(1)(i), 29.923(a),

(b)(1) and (b)(3), 29.1143(f),

29.1305(a)(24) and (a)(25), 29.1521(i)

and (j), and 29.1549(e) and Amendment

36–20 of FAR 36, Appendix H; also

Special Condition No. 96–ASW–16. In

addition, the certification basis includes

certain special conditions, exemptions

and later amended sections of the

applicable Part that are not relevant to

these special conditions.

If the Administrator finds that the

applicable airworthiness regulations for

part 29 do not contain adequate or

appropriate safety standards for the

Sikorsky Model S76C because of a novel

or unusual design feature, special

conditions are prescribed under the

provisions of § 21.16.

In addition to the applicable

airworthiness regulations and special

conditions, the Sikorsky Model S76C

must comply with the noise certification

requirements of part 36, and the FAA

must issue a finding of regulatory

adequacy pursuant to § 611 of Public

Law 92–574, the ‘‘Noise Control Act of

1972.’’

Special conditions, as appropriate, are

issued in accordance with § 11.49, as

required by §§ 11.28 and 11.29(b), and

become part of the type certification

basis in accordance with § 21.101(b)(2).

Special conditions are initially

applicable to the model for which they

are issued. Should the TC for that model

be amended later to include any other

model that incorporates the same novel

or unusual design feature, or should any

other model already included on the

same TC be modified to incorporate the

same novel or unusual design feature,

the special conditions would also apply

to the other model under the provisions

of § 21.101(a)(1).

Novel or Unusual Design Features

The Sikorsky Model S76C will

incorporate the following novel or

unusual design features: A new rated

30-minute power which will require a

special condition for hovering cooling

test procedures and powerplant

limitations.

Applicability

As discussed above, these special

conditions are applicable to the

Sikorsky Model S76C. Should Sikorsky

Aircraft Corporation apply at a later date

for a change to the TC to include

another model incorporating the same

novel or unusual design feature, the

special conditions would apply to that

model as well under the provisions of

§ 21.101(a)(1).

Conclusion

This action affects only certain novel

or unusual design features on one model

of helicopter. It is not a rule of general

applicability and affects only the

applicant who applied to the FAA for

approval of these features on the

helicopter.

Under standard practice, the effective

date of final special conditions would

be 30 days after the date of publication

in the Federal Register; however, as the

certification date for the Sikorsky Model

S76C is imminent, the FAA finds that

good cause exists to make these special

conditions effective upon issuance. The

FAA is requesting comments to allow

interested persons to submit views that

may not have been submitted in

response to the prior opportunities for

comment described above.

List of Subjects in 14 CFR Parts 21 and

29

Aircraft, Air transportation, Aviation

safety, Rotorcraft, Safety.

The authority citation for these

special conditions is as follows:

Authority: 42 U.S.C. 7572; 49 U.S.C.

106(g), 40105, 40113, 44701–44702, 44704,

44709, 44711, 44713, 44715, 45303.

The Special Conditions

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the following special

conditions are issued as part of the type

certification basis for Sikorsky Model

S76C helicopters.

1. Section 29.1049 Hovering Cooling

Test Procedures

In addition to the requirements of

§ 29.1049, acceptable hovering cooling

provisions must be shown for the

following conditions:

(a) At the maximum weight, or at the

greatest weight at which the rotorcraft

can hover (if less), at sea level, with the

power required to hover but not more

than 30-minute power, in-ground effect

in still air, until at least 5 minutes after

the occurrence of the highest

temperature recorded or until the

expiration of the 30-minute power

application period, whichever occurs

first; and,

(b) With 30-minute power, maximum

weight, and at the altitude resulting in

zero rate of climb for this configuration,

until at least 5 minutes after the

occurrence of the highest temperature

recorded or until the expiration of the

30-minute power application period,

whichever occurs first.

2. Section 29.1521 Powerplant

limitations

In addition to the requirements of

§ 29.1521 the limitations for rated 30-

minute power usage must be established

as follows:

Rated 30-Minute Power Operations

The powerplant rated 30-minute

power operation must be limited to use

for periods not to exceed 30 minutes for

hovering operations only and by:

(a) The maximum rotational speed

which may not be greater than—

(i) The maximum value determined

by the rotor design; or

(ii) The maximum value shown

during the type tests;

(b) The maximum allowable turbine

outlet gas temperature;

(c) The maximum allowable engine

and transmission oil temperatures.

(d) The maximum allowable power or

torque for each engine, considering the

power input limitations of the

transmission with all engines operating;

and

(e) The maximum allowable power or

torque for each engine considering the

power input limitations of the

transmission with one-engineinoperative.

Issued in Fort Worth, Texas, on June 5,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service, ASW–100.

[FR Doc. 98–16078 Filed 6–16–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–59–AD; Amendment 39–

10598; AD 98–13–10]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Model 182S

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Cessna Aircraft Company

(Cessna) Model 182S airplanes. This AD

requires repetitively inspecting all

engine exhaust muffler end plates (four
32974 Federal Register / Vol. 63, No. 116 /Wednesday, June 17, 1998 /Rules and Regulations

total) for cracks and replacing any

muffler where an end plate is found

cracked. The AD also requires

fabricating and installing a placard that

specifies immediately inspecting all

engine exhaust muffler end plates any

time the engine backfires upon start-up.

This AD is the result of incidents where

cracks were found in an engine exhaust

muffler end plate on several of the

affected airplanes. These cracks were

caused by high stresses imposed on the

attachment of the exhaust at the area of

the firewall. The actions specified by

this AD are intended to detect and

correct damage to the engine exhaust

mufflers caused by such high stress and

cracking, which could result in exhaust

gases entering the airplane cabin with

consequent crew and passenger injury.

DATES: Effective July 8, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

August 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 98-CE–59-AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Information that relates to this AD

may be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98-CE–59-

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

Kansas City, Missouri 64106.

FOR FURTHER INFORMATION CONTACT: Mr.

Paul Pendleton, Aerospace Engineer,

Wichita Aircraft Certification Office,

FAA, 1801 Airport Road, Mid-Continent

Airport, Wichita, Kansas 67209;

telephone: (316) 946–4143; facsimile:

(316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA has received reports of

incidents where cracks were found in an

engine exhaust muffler end plate on

several Cessna Model 182S airplanes.

These cracks were caused by high

stresses imposed on the attachment of

the exhaust at the area of the firewall.

The design of the Cessna Model 182S

airplanes is such that, during start-up,

the engine could backfire and high

stresses could then be imposed on the

attachment of the exhaust at the area of

the firewall. These high stresses cause

cracks in the engine exhaust muffler end

plates.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

the FAA has determined that AD action

should be taken to detect and correct

damage to the engine exhaust mufflers

caused by such high stress and cracking,

which could result in exhaust gases

entering the airplane cabin with

consequent crew and passenger injury.

Explanation of the Provisions of the AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Cessna Model 182S

airplanes of the same type design, the

FAA is issuing an AD. This AD requires

repetitively inspecting all engine

exhaust muffler end plates (four total)

for cracks and replacing any muffler

where an end plate is found cracked.

The AD also requires fabricating and

installing a placard that specifies

immediately inspecting all engine

exhaust muffler end plates any time the

engine backfires upon start-up.

Compliance Time of This AD

The compliance time of the placard

requirements of this AD is presented in

calendar time instead of hours time-inservice. The chance of the engine

backfiring upon start-up is the same for

airplanes with 25 hours TIS as it is for

airplanes with 100 hours TIS. Therefore,

to assure that the engine exhaust muffler

end plates are inspected any time the

engine backfires upon start-up on all of

the affected airplanes, a compliance

based upon calendar time is utilized.

Determination of the Effective Date of

the AD

Since a situation exists (possible

engine exhaust system damage and

exhaust gases entering the airplane

cabin with consequent crew and

passenger injury) that requires the

immediate adoption of this regulation, it

is found that notice and opportunity for

public prior comment hereon are

impracticable, and that good cause

exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting immediate flight safety and,

thus, was not preceded by notice and

opportunity to comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

will be considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 98–CE–59–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a significant regulatory action

under Executive Order 12866. It has

been determined further that this action

involves an emergency regulation under

DOT Regulatory Policies and Procedures

(44 FR 11034, February 26, 1979). If it

is determined that this emergency

regulation otherwise would be

significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket

(otherwise, an evaluation is not

required). A copy of it, if filed, may be

obtained from the Rules Docket.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the
Federal Register / Vol. 63, No. 116 /Wednesday, June 17, 1998 /Rules and Regulations 32975

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:

98–13–10 Cessna Aircraft Company:

Amendment 39–10598; Docket No. 98–

CE–59–AD.

Applicability: Model 182S airplanes, all

serial numbers, 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 (e) 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 in the

body of this AD, unless already

accomplished.

To detect and correct damage to the engine

exhaust mufflers caused by high stresses

imposed on the attachment of the exhaust at

the area of the firewall and cracking, which

could result in exhaust gases entering the

airplane cabin with consequent crew and

passenger injury, accomplish the following:

(a) Within the next 5 days after the

effective date of this AD, accomplish the

following:

(1) Fabricate a placard that specifies

immediately inspecting all engine exhaust

muffler end plates when the engine backfires

upon start-up, and install this placard on the

instrument panel within the pilot’s clear

view. The placard should utilize letters of at

least 0.10-inch in height and contain the

following words:

‘‘If the engine backfires upon start-up, prior

to further flight, inspect and replace (as

necessary) all engine exhaust muffler end

plates in accordance with AD 98–13–10’’

(2) Insert a copy of this AD into the

Limitations Section of the airplane flight

manual (AFM).

(b) Within the next 25 hours time-inservice (TIS) after the effective date of this

AD and thereafter at intervals not to exceed

25 hours TIS after the previous inspection

(including any inspection accomplished after

an engine backfire), inspect all engine

exhaust muffler end plates (four total) for

cracks on the forward (upstream) or aft

(downstream) end of each muffler can. Prior

to further flight, replace any engine exhaust

muffler where an end plate is found cracked.

The replacement does not eliminate the

repetitive inspection requirement of this AD.

Note 2: Cessna Service Bulletin SB98–78–

02, Issued: June 6, 1998, depicts the area to

be inspected. The actions of this service

bulletin are different from those required by

this AD. This AD takes precedence over the

actions specified in the service bulletin, and

accomplishment of the service bulletin is not

considered an alternative method of

compliance to the actions of this AD. Copies

of this service bulletin may be obtained from

the Cessna Aircraft Company, Product

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

67277.

(c) Fabricating and installing the placard

and inserting this AD into the Limitations

Section of the AFM, as required by paragraph

(a) of this AD, may be performed by the

owner/operator holding at least a private

pilot certificate as authorized by section 43.7

of the Federal Aviation Regulations (14 CFR

43.7), and must be entered into the aircraft

records showing compliance with this AD in

accordance with section 43.9 of the Federal

Aviation Regulations (14 CFR 43.9).

(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) 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, Room 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(f) Information related to this AD may be

examined at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri.

(g) This amendment becomes effective on

July 8, 1998.

Issued in Kansas City, Missouri, on June

10, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–16015 Filed 6–16–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–08–AD; Amendment 39–

10596; AD 98–13–08]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Model PC–12 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Pilatus Aircraft Ltd.

(Pilatus) Model PC–12 airplanes. This

AD requires replacing and re-routing the

power return cables on the starter

generator and generator 2, inserting a

temporary revision to the pilot operating

handbook (POH), and installing a

placard near the standby magnetic

compass. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Switzerland.

The actions specified by this AD are

intended to prevent directional

deviation on the standby magnetic

compass caused by an overload of

electrical current in the airplane

structure, which could result in flightpath deviation during critical phases of

flight in icing conditions and

instrument meteorologic conditions

(IMC).

DATES: Effective July 31, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 31,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Pilatus Aircraft Ltd., Marketing Support

Department, CH–6370 Stans,

Switzerland; telephone: +41 41–6196

233; facsimile: +41 41–6103 351. 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–08–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.

Roman T. Gabrys, Aerospace Engineer,

Small Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone: (816) 426–6934;

facsimile: (816) 426–2169.