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
19810 Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations

from Robinson Helicopter Company,

2901 Airport Drive, Torrance, California

90505. This information may be

examined at the FAA, Office of the

Assistant Chief Counsel, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas

76137, or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Ms.

Elizabeth Bumann, Aerospace Engineer,

FAA, Los Angeles Aircraft Certification

Office, 3960 Paramount Blvd.,

Lakewood, California 90712, telephone

(310) 627–5265, fax (310) 627–5210.

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 Robinson Model

R22 helicopters was published in the

Federal Register on November 28, 1995

(60 FR 58579). That action proposed to

require, within the next 100 hours timein-service (TIS) or 60 calendar days,

whichever comes first, replacement of

the upper sheave, part number (P/N)

A170–1I or J or P/N A170–2J, with a

sheave having a dimension equal to or

less than 0.30 inch measured from the

edge of the forward retainer plate to the

flange of the sheave.

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 650

helicopters of U.S. registry will be

affected by this AD, that it will take

approximately 4 work hours per

helicopter to accomplish the required

actions, and that the average labor rate

is $60 per work hour. Required parts

will cost approximately $1,216 per

helicopter for the sheave, part number

(P/N) A170–1, and $2,298 per helicopter

for the sheave, P/N A170–2. Based on

these figures, the total cost impact of the

AD on U.S. operators is estimated to be

$1,298,050, assuming replacement of

the sheave in all 650 helicopters, and

assuming that one-half of the

helicopters have the sheave, P/N A170–

1, installed, and one-half of the

helicopters have the sheave, P/N A170–

2, installed.

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.

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 to

read as follows:

AD 96–09–29 Robinson Helicopter

Company: Amendment 39–9605. Docket

No. 95–SW–23–AD.

Applicability: Model R22 helicopters with

upper V-belt sheave (sheave) part number (P/

N) A170–1I or J, or P/N A170–2J, installed,

certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (b) 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.

Note 2: Determination of whether the

affected sheave has been installed can be

accomplished by measuring the depth from

the edge of the forward retainer plate to the

flange of the sheave in an area located

between the webs as shown in Figure 2 of

Robinson Helicopter Company R22 Service

Bulletin SB–77, dated April 25, 1995. If the

depth is greater than 0.30 inch, then either

sheave, P/N A170–1I or J, or sheave, P/N

A170–2J, is installed.

Compliance: Required as indicated, unless

accomplished previously.

To prevent failure of the sheave, which

could result in damage to other drive system

components, and subsequent loss of control

of the helicopter, accomplish the following:

(a) Within the next 100 hours time-inservice (TIS) or 60 calendar days, whichever

occurs first after the effective date of this AD,

replace the sheave, P/N A170–1I or J, or P/

N A170–2J, with an airworthy sheave, P/N

A170–1, or P/N A170–2, having a dimension

equal to or less than 0.30 inch measured from

the edge of the forward retainer plate to the

flange of the sheave in an area located

between the webs, in accordance with

paragraphs 2 through 15 of the Compliance

Procedures of Robinson Helicopter Company

R22 Service Bulletin SB–77, dated April 25,

1995.

(b) 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, Los

Angeles Aircraft Certification Office, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Los Angeles 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 Los Angeles Aircraft

Certification Office.

(c) 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.

(d) Replacement of the sheave shall be

done in accordance with paragraphs 2

through 15 of the Compliance Procedures of

Robinson Helicopter Company R22 Service

Bulletin SB–77, dated April 25, 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

Robinson Helicopter Company, 2901 Airport

Drive, Torrance, California 90505. Copies

may be inspected at the FAA, Office of the

Assistant Chief Counsel, 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.

(e) This amendment becomes effective on

June 7, 1996.
Federal Register / Vol. 61, No. 87 / Friday, May 3, 1996 / Rules and Regulations 19811

Issued in Fort Worth, Texas, on April 24,

1996.

Larry M. Kelly,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 96–10870 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 95–CE–27–AD; Amendment 39–

9443; AD 95–24–13]

RIN 2120–AA64

Airworthiness Directives; Jetstream

Aircraft Limited HP137 Mk1, Jetstream

Series 200, and Jetstream Models 3101

and 3201 Airplane; Correction

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This action makes a

correction to Airworthiness Directive

(AD) 95–24–13 concerning Jetstream

Aircraft Limited (JAL) HP137 Mk1,

Jetstream Series 200, and Jetstream

Models 3101 and 3201 airplanes, which

published in the Federal Register on

December 22, 1995 (60 FR 246). That

publication incorrectly references the

number of aileron mounting spigot nut

assemblies to be replaced on the wings

of the airplanes. The AD currently

requires ‘‘replacing the securing nut

assemblies and split pins with new

special nut assemblies (Part No. SL5022

(Qty. 2))’’. The intent of the AD is to

require replacement of 2 special nut

assemblies on each wing, for a total of

4 nut assemblies. The Final Rule AD did

not specify ‘‘each wing’’, and stated that

only 2 nut assemblies rather than 4 nut

assemblies are required. This action

corrects the AD to reflect this change.

EFFECTIVE DATE: January 17, 1996.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

January 17, 1996.

FOR FURTHER INFORMATION CONTACT: Ms.

Dorenda Baker, Program Officer,

Brussels Aircraft Certification Office,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone (322)

508.2715; facsimile (322) 230.6899; or

Mr. Jeffrey Morfitt, Project Officer,

Small Airplane Directorate, Aircraft

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6934;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION: On

November 17, 1995, the Federal

Aviation Administration (FAA) issued

AD 95–24–13, Amendment 39–9443 (60

FR 246, December 22, 1995), which

applies to JAL HP 137 Mk1, Jetstream

series 200, and Jetstream Models 3101

and 3201 airplanes. This AD requires

inspecting (one-time) the threaded

portion of the aileron mounting spigots

for cracks, replacing any cracked

spigots, and replacing the securing nut

assemblies with newly designed special

nut assemblies and new split pins.

Need for the Correction

The AD incorrectly references the

quantity of special nut assemblies,

inferring that a quantity of 2 assemblies

be replaced without indicating that the

2 assemblies on each wing (left wing

and right wing) should be replaced.

Correction of Publication

Accordingly, the publication of

December 22, 1995 (60 FR 246) of

Amendment 39–9443; AD 95–24–13,

which was the subject of FR Doc. 95–

66485, is corrected as follows:

§ 39.13 [Corrected]

On page 66486, in the third column,

section 39.13, paragraph (a), line 1

through line 4, replace ‘‘Inspect the

mounting spigots for cracks using both

visual and fluorescent dye penetrant

methods in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

* * *’’ with ‘‘Inspect the left and right

wing mounting spigots for cracks using

both visual and fluorescent dye

penetrant methods in accordance with

the ACCOMPLISHMENT

INSTRUCTIONS * * *’’.

On page 66486, in the third column,

section 39.13, paragraph (a)(2), line 1

through line 5, replace ‘‘Prior to further

flight, replace the securing nut

assemblies and split pins with new

special nut assemblies (Part No.

SL45022 (Qty. 2)), * * *’’ with ‘‘Prior to

further flight, replace the securing nut

assemblies and split pins on both wings

with new special nut assemblies (Part

No. SL45022 (Qty. of 2 on each wing,

total Qty. of 4 nut assemblies needed)),

* * *’’.

Action is taken herein to clarify this

requirement of AD 95–24–13 and to add

this AD correction to section 39.13 of

the Federal Aviation Regulations (14

CFR 39.13). The effective date remains

January 17, 1996.

Issued in Kansas City, Missouri on April

17, 1996.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 96–11031 Filed 5–2–96; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–CE–37–AD; Amendment 39–

9608; AD 96–10–03]

[RIN 2120–AA64]

Airworthiness Directives; The New

Piper Aircraft, Inc. (Formerly Piper

Aircraft Corporation) PA28, PA32,

PA34, and PA44 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain The New Piper

Aircraft, Inc. (Piper) PA28, PA32, PA34,

and PA44 series airplanes. This action

will require inspecting and modifying

the flap lever assembly. Reports of worn

flap handle attach bolts and elongated

holes in the flap lever to cable mounting

attach point prompted this AD action.

The actions specified by this AD are

intended to prevent failure of the flap

handle attach bolt and sudden retraction

of the flaps, which, if not detected and

corrected, could result in loss of control

of the airplane.

DATES: Effective June 14, 1996.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 14,

1996.

ADDRESSES: Service information that

applies to this AD may be obtained from

The New Piper Aircraft, Inc., Attn:

Customer Service, 2629 Piper Dr., Vero

Beach, Florida 32960. 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–37–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:

Christina Marsh, Aerospace Engineer,

FAA, Atlanta Aircraft Certification

Office, Campus Building, 1701

Columbia Avenue, suite 2–160, College

Park, Georgia 30337–2748; telephone

(404) 305–7362; facsimile (404) 305–

7348.

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 The

New Piper Aircraft, Inc. (Piper) PA28,

PA32, PA34, and PA44 series airplanes

was published in the Federal Register

on October 13, 1995 (60 FR 53314). The

action proposed to require inspecting