Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations 19807

By order of the Board of Governors of the

Federal Reserve System, April 26, 1996.

Jennifer J. Johnson,

Deputy Secretary of the Board.

[FR Doc. 96–10891 Filed 5–2–96; 8:45 am]

BILLING CODE 6210–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–47–AD; Amendment 39–

9578; AD 96–09–04]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–3 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 90–12–08,

which currently requires the following

on de Havilland Model DHC–3

airplanes: repetitively inspecting (using

dye penetrant methods) the tailplane

main rib forward flanges and the main

rib forward lower flanges at the

tailplane front attachment fitting for

cracks and repairing any cracked flange.

This AD action will retain the repetitive

inspections currently required by AD

90–12–08, and will allow a certain

modification as terminating action for

these repetitive inspections. This action

is prompted by the Federal Aviation

Administration’s determination that

installing new angles and plates on the

tailplane root ribs on de Havilland

Model DHC–3 airplanes provides an

equivalent level of safety to the

repetitive inspections required by AD

90–12–08. The actions specified by this

AD are intended 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.

DATES: Effective May 17, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 17,

1996.

ADDRESSES: Service information that

applies to this AD 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. 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–47–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.

Jeff Casale, Aerospace Engineer, FAA,

New York Aircraft Certification Office,

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

New York 11581; telephone (516) 256–

7521; facsimile (516) 568–2716.

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 de

Havilland Model DHC–3 airplanes was

published in the Federal Register on

November 14, 1995 (60 FR 57201). This

action would retain the repetitive

inspections currently required by AD

90–12–08, and would allow

incorporating a certain modification as

terminating action for these repetitive

inspections. Accomplishment of this

action will be in accordance with de

Havilland Service Bulletin (SB) No. 3/

46, Revision B, dated December 1, 1989

and de Havilland SB No. 3/50, Revision

A, dated February 17, 1995.

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 49 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

35 workhours per airplane to

accomplish the inspection and that the

average labor rate is approximately $60

an hour. Based on these figures, the total

cost impact of this AD on U.S. operators

is estimated to be $102,900 or $2,100

per airplane. This figure represents the

cost of the initial inspection, and does

not reflect the costs for repetitive

inspections or possible repairs. The

FAA has no way of determining how

many tailplane main rib forward or

main rib forward lower flanges may

need to be repaired or how many

repetitive inspections each owner/

operator of the affected airplanes would

incur over the life of the airplane.

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

removing AD 90–12–08, Amendment

39–6622, and by adding a new

airworthiness directive (AD) to read as

follows:

96–09–04 De Havilland: Amendment 39–

9578. Docket No. 95–CE–47–AD;

Supersedes AD 90–12–08, Amendment

39–6622.

Applicability: Model DHC–3 airplanes (all

serial numbers), certificated in any category,

that do not have Modification 3/935

incorporated in accordance with de

Havilland Service Bulletin (SB) number (No.)

3/50, Revision A, dated February 17, 1995.
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