19808 Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations

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: Within the next 3 calendar

months after the effective date of this AD,

unless already accomplished (compliance

with AD 90–12–08), and thereafter at

intervals not to exceed 24 calendar months.

To prevent failure of the tailplane structure

caused by cracked tailplane main rib forward

flanges or main rib forward lower flanges at

the tailplane front attachment fitting, which,

if not detected and corrected, could result in

loss of control of the airplane, accomplish the

following:

(a) Inspect, using dye penetrant methods,

the tailplane main rib forward flanges and

the main rib forward lower flanges at the

tailplane front attachment fitting in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of de Havilland SB

No. 3/46, Revision B, dated December 1,

1989.

Note 2: Pay particular attention to the front

attachment fitting area.

(b) Prior to further flight, repair any

tailplane main rib forward flange or main rib

forward lower flange found cracked during

any inspection required by this AD.

Accomplish this repair in accordance with

the ACCOMPLISHMENT INSTRUCTIONS

section of de Havilland SB No. 3/46, Revision

B, dated December 1, 1989.

(c) Installing tailplane root rib angles and

plates of improved design (Modification 3/

935) in accordance with de Havilland SB 3/

50, Revision A, dated February 17, 1995,

terminates the repetitive inspection

requirement of this AD. Modification 3/935

may be incorporated at any time provided

that any tailplane main rib forward flange or

main rib forward lower flange found cracked

during any inspection required by this AD is

repaired.

(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 initial or repetitive

compliance times that provides an equivalent

level of safety may be approved by the

Manager, New York Aircraft Certification

Office, 10 5th St., 3rd Floor, Valley Stream,

New York 11581. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

New York Aircraft Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the New York Aircraft

Certification Office.

(f) Alternative methods of compliance

approved in accordance with AD 90–12–08

(superseded by this action) are considered

approved as alternative methods of

compliance with this AD.

(g) The inspections, repairs, and

replacements required by this AD shall be

done in accordance with de Havilland

Service Bulletin No. 3/46, Revision B, dated

December 1, 1989, and de Havilland Service

Bulletin No. 3/50, Revision A, dated

February 17, 1995. 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 Bombardier Inc. (the parent

company of de Havilland), Bombardier

Regional Aircraft Division, Garrett Boulevard,

Downsview, Ontario, Canada M3K 1Y5;

telephone (416) 633–7310. Copies may be

inspected at the FAA, Central Region, Office

of the Assistant Chief Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri, or

at the Office of the Federal Register, 800

North Capitol Street, NW., 7th Floor, suite

700, Washington, DC.

(h) This amendment supersedes AD 90–

12–08, Amendment 39–6622.

(i) This amendment (39–9578) becomes

effective on May 17, 1996.

Issued in Kansas City, Missouri, on April

18, 1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–10076 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–50–AD; Amendment 39–

9585; AD 96–09–09]

RIN 2120–AA64

Airworthiness Directives; I.A.M.

Rinaldo Piaggio S.p.A. Model P 180

Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to I.A.M. Rinaldo Piaggio S.p.A.

Model P 180 series airplanes. This

action requires installing a shield on the

front section of the engine cradle. A

report of power control jamming as a

result of freezing conditions during a

high altitude flight prompted this AD

action. The actions specified by this AD

are intended to prevent loss of engine

power or the propeller controls from

jamming as a result of freezing rain

entering the engine nacelle, which, if

not detected and corrected, could result

in loss of control of the airplane.

DATES: Effective June 7, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 7,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

I.A.M. Rinaldo Piaggio, S.p.A., Via

Cibrario, 4 16154, Genoa, Italy. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket 95–CE–50–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: Ms.

Dorenda Baker, Program Manager,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322) 513–

3830, ext. 2716; facsimile (322) 230–

6899; or Mr. Roman T. Gabrys, Project

Officer, Small Airplane Directorate,

Airplane Certification Service, FAA,

1201 Walnut, suite 900, Kansas City,

Missouri 64105; telephone (816) 426–

6932; facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an AD that would apply to

I.A.M. Rinaldo Piaggio S.p.A. Model P

180 series was published in the Federal

Register on October 4, 1995 (60 FR

51944). The action proposed to require

installing a shield on the front section

of the engine cradle. Accomplishment of

this action would be in accordance with

Piaggio Service Bulletin (SB) 80–0066;

Original Issue December 12, 1994.

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.

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.

The FAA estimates that 5 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 2
Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations 19809

workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

will be furnished by the manufacturer at

no cost to the owner/operators. Based

on these figures, the total cost impact of

this AD on U.S. operators is estimated

to be $600. This figure is based on the

assumption that none of the affected

airplanes have shields installed and that

none of the affected owners/operators

have modified the airplanes.

The compliance time of this AD is

presented in both hours time-in-service

(TIS) and calendar time. The FAA has

determined that including calendar time

compliance is also necessary because

the unsafe condition is the result of

adverse weather conditions which can

affect the nacelle and power controls

while not in use as well as in flight.

Therefore, to ensure that the abovedescribed condition is detected and

corrected on all airplanes within a

reasonable period of time without

inadvertently grounding any airplanes, a

compliance schedule based upon both

TIS and calendar time is required.

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:

96–09–09 I.A.M. Rinaldo Piaggio S.P.A.:

Amendment 39–9585; Docket No. 95–

CE–50–AD.

Applicability: Model P 180 Series

Airplanes (serial numbers 1001, 1002, 1004,

and 1006 through 1033), 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 within the next 100

hours time-in service (TIS), or within the

next 3 calendar months, whichever occurs

later, after the effective date of this AD,

unless already accomplished.

Note 2: The compliance time in this AD

takes precedence over the compliance time

reflected in Piaggio Service Bulletin 80–0066,

Original Issue, December 12, 1994.

To prevent loss of engine power or the

propeller controls from jamming, as a result

of freezing rain entering the engine nacelle,

which, if not detected and corrected, could

result in loss of control of the airplane,

accomplish the following:

(a) Modify the nacelle by installing a shield

on the front section of the engine cradle, in

accordance with the ACCOMPLISHMENT

INSTRUCTIONS section in Piaggio Service

Bulletin (SB) No. 80–0066; Original Issue:

December 12, 1994.

(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, Brussels Aircraft

Certification Office, FAA, Europe, Africa, and

Middle East Office, c/o American Embassy,

B–1000 Brussels, Belgium or Mr. Roman T.

Gabrys, Project Officer, Small Airplane

Directorate, Airplane Certification Service,

FAA, 1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Brussels Aircraft Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Brussels Aircraft

Certification Office.

(d) The modifications required by this AD

shall be done in accordance with Piaggio

Service Bulletin No. 80–0066; Original Issue:

December 12, 1994. 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 I.A.M. Rinaldo Piaggio, S.p.A.,

Via Cibrario, 4 16154, Genoa, Italy. Copies

may be inspected at the FAA, Central Region,

Office of the Assistant Chief 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 (39–9585) becomes

effective on June 7, 1996.

Issued in Kansas City, Missouri, on April

23, 1996.

Henry A. Armstrong,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 96–10581 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–SW–23–AD; Amendment

39–9605; AD 96–09–29]

Airworthiness Directives; Robinson

Helicopter Company Model R22

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Robinson Helicopter

Company (Robinson) Model R22

helicopters, that requires replacement of

the upper V-belt sheave (sheave). This

amendment is prompted by three

reports of cracks in the flange of the

sheave. The actions specified by this AD

are intended to prevent failure of the

sheave, which could result in damage to

other drive system components, and

subsequent loss of control of the

helicopter.

DATES: Effective June 7, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 7,

1996.

ADDRESSES: The service information

referenced in this AD may be obtained