6890 Federal Register / Vol. 62, No. 31 / Friday, February 14, 1997 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Jetstream Aircraft Limited: Docket 96–NM–

168–AD.

Applicability: Model 4101 airplanes,

constructors numbers 41004 through 41086

inclusive; 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 (d) 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, unless

accomplished previously.

To prevent cracking in frame 179 of the

fuselage, which could result in structural

failure of the fuselage and consequent rapid

decompression of the pressurized section of

the fuselage, accomplish the following:

(a) Prior to the accumulation of 3,000 total

flight cycles, or within 300 flight cycles after

the effective date of this AD, whichever

occurs later, perform a detailed visual

inspection to detect cracks on frame 179 at

the attachment bracket for the door restraint

cable, in accordance with Part 1 of the

Accomplishment Instructions of Jetstream

Alert Service Bulletin J41–A53–024, dated

April 26, 1996.

(1) If no crack is detected, repeat the visual

inspection thereafter at intervals not to

exceed 1,000 flight cycles. After each

inspection, perform the actions specified in

paragraph (c) of this AD.

(2) If any crack is detected, prior to further

flight, repair it in accordance with a method

approved by the Manager, Standardization

Branch, ANM–113, FAA, Transport Airplane

Directorate. After repair, perform the actions

specified in paragraph (c) of this AD.

(b) Within 24 months after the effective

date of this AD, perform the visual inspection

specified in paragraph (a) of this AD in

accordance with Part 2 of the

Accomplishment Instructions of Jetstream

Alert Service Bulletin J41–A53–024, dated

April 26, 1996; and accomplish the

applicable follow-on actions specified in

paragraph (b)(1) or (b)(2) of this AD.

(1) If no crack is detected, prior to further

flight, install new doublers and stress pads

on frame 179 in accordance with the alert

service bulletin. Immediately after

installation, perform the actions specified in

paragraph (c) of this AD. Accomplishment of

these actions constitutes terminating action

for the repetitive inspection requirements of

paragraphs (a)(1) of this AD.

(2) If any crack is detected, prior to further

flight, repair it in accordance with a method

approved by the Manager, Standardization

Branch. Prior to further flight following

accomplishment of the repair, install new

doublers and stress pads on frame 179 in

accordance with the alert service bulletin;

and then perform the actions specified in

paragraph (c) of this AD. Accomplishment of

these actions constitutes terminating action

for the repetitive inspection requirements of

paragraphs (a)(1) of this AD.

(c) Prior to further flight following

accomplishment of the actions as specified in

paragraph (a)(1), (a)(2), (b)(1), or (b)(2) of this

AD, perform a test to verify proper

adjustment of the restraint cable, in

accordance with the alert service bulletin. If

the restraint cable has been improperly

adjusted, prior to further flight, correct the

discrepancy in accordance with the alert

service bulletin.

(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,

Standardization Branch. Operators shall

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, Standardization Branch, ANM–113.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Standardization Branch,

ANM–113.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

Issued in Renton, Washington, on February

5, 1997.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–3691 Filed 2–13–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–CE–62–AD]

RIN 2120–AA64

Airworthiness Directives; Industrie

Aeronautiche E Meccaniche Model

Piaggio P–180 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes to

adopt a new airworthiness directive

(AD) that would apply to certain

Industrie Aeronautiche E Meccaniche

(I.A.M.) Model Piaggio P–180 airplanes

that are equipped with a certain freon

air conditioning system. The proposed

action would require inspecting the

baggage compartment for stringer or air

cycle machine (ACM) by-pass duct

damage, repairing any damage found,

and modifying the freon air inlet duct

and electrical wiring. The proposed AD

results from trim system malfunction on

one of the affected airplanes, resulting

from contact between the freon air inlet

duct and the electrical wiring. The

actions specified by the proposed AD

are intended to prevent trim system

malfunction caused by contact between

the freon air inlet duct and electrical

wiring, which could result in loss of

control of the airplane.

DATES: Comments must be received on

or before April 25, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Assistant Chief Counsel,

Attention: Rules Docket No. 96–CE–62–

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

Kansas City, Missouri 64106. Comments

may be inspected at this location

between 8 a.m. and 4 p.m., Monday

through Friday, holidays excepted.

Service information that applies to the

proposed AD may be obtained from

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

Cibrario, 4 16154, Genoa, Italy. This

information also may be examined at

the Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr.

Maurice Kuttler, Program Manager,

Brussels Aircraft Certification Division,

FAA, Europe, Africa, and Middle East

Office, c/o American Embassy, B–1000

Brussels, Belgium; telephone 32 2 508

2715; facsimile 32 2 230 6899; or Mr.

Roman T. Gabrys, Project Officer, Small

Airplane Directorate, Airplane

Certification Service, FAA, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone (816) 426–6932;

facsimile (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed 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, specified

above, will be considered before taking

action on the proposed rule. The

proposals contained in this notice may

be changed in light of the comments

received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by
Federal Register / Vol. 62, No. 31 / Friday, February 14, 1997 / Proposed Rules 6891

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 96–CE–62–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Central Region, Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 96–CE–62–AD, Room

1558, 601 E. 12th Street, Kansas City,

Missouri 64106.

Discussion

The Registro Aeronautico Italiano

(RAI), which is the airworthiness

authority for Italy, recently notified the

FAA that an unsafe condition may exist

on I.A.M. Model Piaggio P–180

airplanes. The RAI reports trim system

malfunction on one of the affected

airplanes, resulting from contact

between the freon air inlet duct and the

electrical wiring. The affected airplane

was equipped with a freon air

conditioning system incorporated in

accordance with I.A.M. Kit 80KS00004–

* * *(801/803/805/807). This same

configuration exists on I.A.M. Model

Piaggio P–180 airplanes equipped with

a Keith Freon Air Conditioning System

installed in accordance with

Supplemental Type Certificate (STC)

SA2762CE. This condition, if not

detected and corrected, could result in

airplane controllability problems if use

of the trim system was lost or the system

malfunctioned.

Applicable Service Information

I.A.M. has issued Piaggio Avante P–

180 Service Bulletin (SB) 80–00083,

Original Issue: December 7, 1994;

Revision No. 1: December 5, 1995,

which includes procedures for the

following on Model Piaggio P–180

airplanes:

—Inspecting the baggage compartment

to verify if damage has occurred to a

stringer and to the Air Cycle Machine

(ACM) by-pass duct because of

chafing with the freon air inlet duct;

and

—Protecting the tubings/hoses in the

electrical wiring (Modification No.

80M000014).

I.A.M. started incorporating

Modification No. 80M000014 on Model

Piaggio P–180 airplanes during

manufacture, beginning with serial

number 1031.

The RAI classified Piaggio Avante P–

180 SB 80–00083 as mandatory and

issued RAI AD 96–042, dated February

21, 1996, in order to assure the

continued airworthiness of these

airplanes in Italy.

Evaluation of all Applicable

Information

This airplane model is manufactured

in Italy and is type certificated for

operation in the United States under the

provisions of § 21.29 of the Federal

Aviation Regulations (14 CFR 21.29)

and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the RAI has kept the FAA informed of

the situation described above.

The FAA has examined the findings

of the RAI; reviewed all available

information, including the service

information referenced above; and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other I.A.M. Model Piaggio

P–180 airplanes of the same type design

that are registered in the United States

and have either a freon air conditioning

system incorporated in accordance with

I.A.M. Kit 80KS00004–* * * (801/803/

805/807) or a Keith Freon Air

Conditioning System installed in

accordance with STC SA2762CE, the

FAA is proposing AD action. The

proposed AD would require inspecting

the baggage compartment for stringer or

air cycle machine (ACM) by-pass duct

damage and repairing any damage

found; and modifying the freon air inlet

duct and electrical wiring (Modification

No. 80M000014). Accomplishment of

the proposed inspection and

modification would be in accordance

with Piaggio Avante P–180 SB 80–

00083, Original Issue: December 7,

1994; Revision No. 1: December 5, 1995.

Cost Impact

The FAA estimates that 5 airplanes in

the U.S. registry would be affected by

the proposed AD, that it would take

approximately 18 workhours

(inspection: 2 workhours; modification:

16 workhours) per airplane to

accomplish the proposed action, and

that the average labor rate is

approximately $60 an hour. Parts will

cost approximately $100 per airplane.

Based on these figures, the total cost

impact of the proposed AD on U.S.

operators is estimated to be $5,900 or

$1,180 per airplane.

The above figures only take into

account the cost of the inspection and

modification, and do not account for the

cost of replacing any parts found

damaged during the inspection. The

FAA has no way of determining how

many airplanes may find damage during

the inspections (if mandated through

final rule AD action).

The FAA knows of no affected

airplane owner/operator (of the five

affected) that has already accomplished

the proposed action.

Regulatory Impact

The regulations proposed herein

would 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

proposal would 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) if

promulgated, 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 draft

regulatory evaluation prepared for this

action has been placed 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, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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), 40101, 40113,

44701.
6892 Federal Register / Vol. 62, No. 31 / Friday, February 14, 1997 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding a new airworthiness directive

(AD) to read as follows:

Industrie Aeronautiche E Mecchaniche:

Docket No. 96–CE–62–AD.

Applicability: Model Piaggio P–180

airplane, serial numbers 1004 and 1006

through 1030, certificated in any category,

that have either a freon air conditioning

system incorporated in accordance with

I.A.M. Kit 80KS00004-*** (801/803/805/807)

or a Keith Freon Air Conditioning System

installed in accordance with Supplemental

Type Certificate (STC) SA2762CE.

Note 1: The modification required by this

AD is incorporated at manufacture on Model

Piaggio P–180 airplanes, beginning with

serial number 1031. Airplanes with this

modification are not affected by this AD.

Note 2: 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 (d) 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 after the effective date

of this AD, unless already accomplished.

To prevent trim system malfunction caused

by contact between the freon air inlet duct

and electrical wiring, which could result in

loss of control of the airplane, accomplish the

following:

(a) Inspect the baggage compartment for

stringer or air cycle machine (ACM) by-pass

duct damage (cracks, frays, nicks, dents, etc.)

in accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Piaggio Avante P–

180 Service Bulletin (SB) 80–00083, Original

Issue: December 7, 1994; Revision No. 1:

December 5, 1995. If any parts are damaged,

prior to further flight, repair or replace the

damaged part in accordance with the

applicable maintenance manual.

(b) Modify the freon air inlet duct and

electrical wiring (Modification No.

80M000014) in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of Piaggio Avante P–180 SB 80–

00083, Original Issue: December 7, 1994;

Revision No. 1: December 5, 1995.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(d) 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 Division, FAA, Europe, Africa,

and Middle East Office, c/o American

Embassy, B–1000 Brussels, Belgium. 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

Division.

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 Division.

(e) All persons affected by this directive

may obtain copies of the documents referred

to herein upon request to I.A.M. Rinaldo

Piaggio, S.p.A., Via Cibrario, 4 16154, Genoa,

Italy; or may examine these documents at the

FAA, Central Region, Office of the Assistant

Chief Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri 64106.

Issued in Kansas City, Missouri, on

February 7, 1997.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 97–3692 Filed 2–13–97; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 96–NM–188–AD]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAC 1–11 200 and

400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

British Aerospace Model BAC 1–11 200

and 400 series airplanes. This proposal

would require repetitive ultrasonic

inspections to detect cracking of the

lugs of the engine mounting beams, and

replacement of the beam with a

serviceable part, if necessary. This

proposal is prompted by reports of

fatigue cracking of the lugs of the engine

mounting beams. The actions specified

by the proposed AD are intended to

detect and correct such cracking of the

engine mounting lugs, which could

result in reduced structural capability of

the engine mount.

DATES: Comments must be received by

March 27, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 96–NM–

188–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

British Aerospace, Airbus Limited, P.O.

Box 77, Bristol BS99 7AR, England. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT: Tim

Backman, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2797; fax (206) 227–1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

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, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed 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

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 96–NM–188–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–103, Attention: Rules Docket No.

96–NM–188–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for