34800 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (d) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required before further flight,

unless accomplished previously.

To prevent loss of the tip fairing on the

blade, which could result in increased

vibrations, loss of the tail rotor assembly, and

subsequent loss of control of the helicopter,

accomplish the following:

(a) Perform a one-time inspection of each

tail rotor blade for debonds. The area to be

inspected is located in a spanwise band from

620.0 mm to 670.0 mm (24.4 to 26.4 inches),

as measured outboard from the blade

retention bolt centerline. Inspect the entire

blade surface on both sides of each blade

within this band (see Figure 1).

Note 2: Agusta Bollettino Tecnico

(Technical Bulletin) Number 109K–15,

Revision A, dated April 18, 1997, pertains to

the subject of this AD.

(b) Perform a tapping inspection to detect

debonds within the blade surface area

identified in paragraph (a) of this AD, using

an aluminum hammer, P/N 109–3101–58–2,

or equivalent. The presence of paint cracks

on the tail rotor blade upper or lower surface

in the tip fairing area at the 670.0 mm

spanwise location (see Figure 1) may indicate

that debonds exist.

(c) Any blade that does not meet the

allowable debond criteria specified in the

applicable maintenance manual must be

replaced with an airworthy blade before

further flight.

(d) 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, FAA,

Rotorcraft Directorate, Rotorcraft Standards

Staff. Operators shall submit their requests

through an FAA Principal Maintenance

Inspector, who may concur or comment and

then send it to the Manager, Rotorcraft

Standards Staff.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(e) 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 helicopter

to a location where the requirements of this

AD can be accomplished.

(f) This amendment becomes effective on

July 13, 1998.

Note 4: The subject of this AD is addressed

in Registro Aeronautico Italiano (Italy) AD

97–124 and AD 97–125, both dated April 30,

1997.

Issued in Fort Worth, Texas, on June 15,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–16612 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–60–AD; Amendment 39–

10634; AD 98–13–41]

RIN 2120–AA64

Airworthiness Directives; Cessna

Aircraft Company Model 172R

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Cessna Aircraft

Company (Cessna) Model 172R

airplanes. This action requires:

inspecting for incorrectly routed aileron

control cables in the center console area;

inspecting for incorrectly routed aileron

control cables in the right-hand (RH)
Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations 34801

wing area; inspecting for a loose or

improperly installed center lock clamp

on the forward aileron control cable

drum; and inspecting for loose or

missing elevator trim actuator mounting

screws, loose rudder circuit pulleys,

missing rudder cable guard pins,

incorrect elevator trim cable routing,

aileron control cable clearance, and

flight control cable tension or rigging

outside specification. If any of the above

conditions are found, this AD requires

correcting, repairing, or replacing any

damaged or missing part, and reporting

any of the above conditions found to the

Wichita Aircraft Certification Office.

Notification by the manufacturer,

service difficulty reports (SDR’s), and an

FAA surveillance audit at the

manufacturing facility identifying

potential deficiencies on the affected

airplanes prompted the action. The

actions specified by this AD are

intended to prevent loss of aileron and

elevator control, which could result in

loss of directional control of the

airplane.

DATES: Effective July 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

August 18, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–60–

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

Kansas City, Missouri 64106.

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. 98–CE–60–

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.

Joel M. Ligon, Aerospace Engineer,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Rm. 100,

Mid-Continent Airport, Wichita, Kansas,

67209, telephone: (316) 946–4138;

facsimile: (316) 946–4407.

SUPPLEMENTARY INFORMATION:

Discussion

The FAA has recently been notified

by Cessna Aircraft Company of a quality

control problem in the aileron and

elevator control systems on certain

Cessna Model 172R airplanes. In

addition to this disclosure, the FAA has

received service difficulty reports

(SDR’s) from the field regarding aileron

cable control malfunction. The FAA

also completed a surveillance audit

revealing airplanes having incorrectly

routed aileron cables, mis-rigged aileron

and elevator control cables, and missing

parts in the aileron and elevator

systems.

Relevant Service Information

Cessna has issued the following

service bulletins applicable to certain

Cessna Model 172R airplanes:

—SB98–27–02, dated May 11, 1998,

which specifies procedures for

inspecting for incorrect routing of the

aileron cable over the cable guard in

the center console area, or fraying of

the cable. If incorrect routing is found

and the cable is frayed, the service

bulletin specifies replacing the cable

with a new cable. If incorrect routing

is found, but no evidence of fraying is

found, the service bulletin specifies

re-routing the cable to its correct

position;

—SB98–27–05, dated June 1, 1998,

which specifies procedures for

inspecting the aileron control cable in

the right-hand (RH) wing for routing

over an aileron autopilot actuator

pulley instead of the aileron flight

control pulley in the adjacent location

and contains instructions to remove

the aileron autopilot actuator pulley.

If the aileron control cable is routed

over the autopilot actuator pulley and

the cable is frayed or damaged,

replace the aileron control cable. If

mis-routing is found, but no evidence

of fraying is found, the service

bulletin specifies re-routing the cable

to its proper position;

—SB98–27–03, dated June 1, 1998,

which specifies procedures for

inspecting for a loose or incorrectly

installed aileron control cable

centering and retainer lock clamp on

the forward aileron control cable

drum. This condition can result in the

primary aileron cable dislodging on

the drum which could cause damage

to the drum and/or partial or

complete loss of aileron control. If

this condition is found, repair or

replace any damaged part; and,

—SB98–27–06, dated June 15, 1998,

which specifies procedures for

inspecting for loose or missing

elevator trim actuator mounting

screws, loose rudder circuit pulleys,

missing rudder cable guard pins,

incorrect routing of the elevator trim

cable, incorrect aileron crossover

cable clearance, and incorrect

specifications of the flight control

cable tension and rigging. If any of the

above conditions are found, the

service bulletin specifies repairing,

replacing, or correcting the part that is

damaged, out of alignment, or misrigged.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the relevant service

information, the FAA has determined

that AD action should be taken to

prevent loss of aileron and elevator

control, which could result in loss of

directional control of the airplane.

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 172R

airplanes of the same type design, this

AD requires:

—Inspecting for incorrectly routed

aileron control cable in the center

console area;

—Inspecting for incorrectly routed

aileron control cable in the right-hand

(RH) wing area;

—Inspecting for a loose or incorrectly

installed center lock clamp on the

forward aileron control cable drum;

—Inspecting for loose or missing

elevator trim actuator mounting

screws, loose rudder circuit pulleys,

missing rudder cable guard pins,

improper elevator trim cable routing,

aileron control cable clearance, and

flight control cable tension rigging

outside specification; and

—If any of the above conditions are

found, this AD would require

correcting the condition, repairing or

replacing any damaged or missing

part, and reporting any condition

found to the Wichita Manufacturing

Inspection Office.

The inspections are to be done in

accordance with the Accomplishment

Instructions contained in Cessna Service

Bulletins (SB) SB98–27–02, dated May

11, 1998, SB98–27–03, dated June 1,

1998, SB98–27–05, dated June 1, 1998,

and SB98–27–06, dated June 15, 1998,

whichever is applicable.

Determination of the Effective Date of

the AD

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for public prior comment
34802 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations

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–60–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, 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:

98–13–41 Cessna Aircraft Company:

Amendment 39–10634; Docket No. 98–

CE–60–AD.

Applicability: Model 172R airplanes with

serial numbers 17280001 through 17280475

and 17280506, 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 (g) 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 25

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

date of this AD, unless already accomplished.

To prevent loss of aileron and elevator

control, which could result in loss of

directional control of the airplane,

accomplish the following:

Note 2: Some airplane serial numbers may

appear in all of the actions required by this

AD and some airplane serial numbers may

only appear in one action required by this

AD. It is recommended to look at each group

of serial numbers closely.

(a) For Cessna Model 172R airplanes with

serial numbers 17280001 through 17280326,

17280328, 17280330 through 17280335,

17280337, 17280339 through 17280342,

17280345, 17280346, 17280350, 17280353

through 17280359, 17280361 through

17280364, 17280366, 17280367, 17280371,

17280377, 17280380 through 17280383,

17280385, 17280387,17280390, 17280391,

17280393, 17280397, 17280423, 17280432

through 17280434, 17280440, 17280441,

17280457, 17280460, 17280461, 17280465

through 17280470, and 17280474:

(1) Inspect the aileron control cables in the

center console area for incorrect routing over

the cable guard, fraying or damage in

accordance with the Accomplishment

Instructions in Cessna Service Bulletin (SB)

No. SB98–27–02, dated May 11, 1998.

(2) Prior to further flight, re-route any

aileron control cable found out of place, and

replace any aileron control cable found

frayed or damaged in accordance with the

Accomplishment Instructions in Cessna SB

No. SB98–27–02, dated May 11, 1998.

(b) For Cessna Model 172R airplanes with

serial numbers 17280002, 17280004,

17280021, 17280024, 17280069 through

17280073, 17280075, 17280077, 17280079

through 17280081, 17280083, 17280086,

17280092, 17280095, 17280109, 17280114,

17280120 through 17280124, 17280127,

17280133, 17280136, 17280147, 17280148,

17280150, 17280159, 17280163, 17280171,

17280207, 17280214, 17280224, 17280234,

17280239, 17280242, 17280248, 17280251,

17280253, 17280257, 17280262, 17280275,

17280281, 17280282, 17280285, 17280287,

17280292, 17280301, 17280305, 17280329,

17280337, 17280338, 17280341, 17280342,

17280343, 17280345, 17280351, 17280354,

17280356, 17280357, 17280359, 17280365,

17280429, and 17280506 that were not

factory equipped with an autopilot:

(1) Inspect the right-hand wing for an

incorrectly routed aileron control cable in

accordance with the Accomplishment

Instructions in Cessna SB No. SB98–27–05,

dated June 1, 1998.

(2) If the aileron control cable is misrouted, prior to further flight, correct the

routing, and if there is fraying or damage to

the aileron control cable, prior to further

flight, replace the control cable in accordance

with the Accomplishment Instructions in

Cessna SB No. SB98–27–05, dated June 1,

1998.

(c) For Cessna Model 172R airplanes with

serial numbers 17280001 through 17280349:

(1) Inspect for a loose or incorrectly

installed center lock clamp on the forward

aileron control cable drum in accordance

with the Accomplishment Instructions in

Cessna SB No. SB98–27–03, dated June 1,

1998.

(2) If the center lock clamp is loose or is

installed incorrectly, prior to further flight,

correct and adjust appropriately in

accordance with the Accomplishment

Instructions in Cessna SB No. SB98–27–03,

dated June 1, 1998.

(d) For Cessna Model 172R airplanes with

serial numbers 17280001 through 17280475:
Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations 34803

(1) Inspect for loose or missing elevator

trim actuator mounting screws, loose rudder

circuit pulleys, missing rudder cable guard

pins, incorrect elevator trim cable routing,

aileron control cable clearance, and flight

control cable tension or rigging outside the

design specifications in accordance with the

Accomplishment Instructions in Cessna SB

No. SB98–27–06, dated June 15, 1998.

(2) If any condition in paragraph (d)(1) of

this AD is found, prior to further flight,

repair, replace, or correct in accordance with

the Accomplishment Instructions in Cessna

SB No. SB98–27–06, dated June 15, 1998.

(e) If any of the conditions noted above in

paragraphs (a), (b), (c), or (d) of this AD are

found within 10 days of the inspection,

report the condition found, date of

inspection, and the serial number of the

airplane to Doyle M. King, Jr., Manager,

Wichita Manufacturing Inspection, Office,

1801 Airport Road, Rm. 101, Mid-Continent

Airport, Wichita, Kansas, 67209. Reporting

requirements have been approved by the

Office of Management and Budget and

assigned OMB control number 2120–0056.

(f) 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.

(g) 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(h) The inspections, repairs, replacements,

adjustments, and corrections required by this

AD shall be done in accordance with Cessna

Service Bulletins No. SB98–27–02, dated

May 11, 1998, No. SB98–27–03, dated June

1, 1998, No. SB98–27–05, dated June 1, 1998,

and No. SB98–27–06, dated June 15, 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 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.

(i) This amendment becomes effective on

August 18, 1998.

Issued in Kansas City, Missouri, on June

19, 1998.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–17020 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–06–AD; Amendment

39–10631; AD 98–13–40]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA 330F, G, and J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

SA 330F, G, and J helicopters, that

requires verifying the torque on the nut

that secures the two transformerrectifiers’ common ground; and

subsequently installing a modification

to separate the grounds of the two

transformer-rectifiers. This amendment

is prompted by a report from the

airworthiness authority of France about

an unsafe condition resulting from the

loss of the common ground of the two

transformer-rectifiers. The actions

specified by this AD are intended to

prevent loss of the common ground of

the two transformer-rectifiers, which

could result in a complete electrical

failure (essential and secondary), loss of

electrically-powered instrumentation,

and subsequent loss of control of the

helicopter.

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: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Carroll Wright, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Regulations Group, 2601 Meacham

Blvd., Fort Worth, Texas 76137,

telephone (817) 222–5120, fax (817)

222–5961.

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 Eurocopter France

Model SA 330F, G, and J helicopters

was published in the Federal Register

on March 5, 1998 (63 FR 10783). That

action proposed to require verifying the

torque on the nut that secures the two

transformer-rectifiers’ common ground;

and subsequently installing a

modification to separate the grounds of

the two transformer-rectifiers.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 1 helicopter

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 0.5 work hour to verify

or accomplish the retorque of the nut, 2

work hours per helicopter to accomplish

the proposed modifications, and that the

average labor rate is $60 per work hour.

Required parts for the modification

would cost approximately $70 per

helicopter. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be $220.

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.