[Federal Register Volume 62, Number 36 (Monday, February 24, 1997)]
[Proposed Rules]
[Pages 8196-8198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-4371]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-56-AD]
RIN 2120-AA64


Airworthiness Directives; I. A. M. Rinaldo Piaggio Model P180 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes to adopt a new airworthiness directive 
(AD) that would apply to certain I. A. M. Rinaldo Piaggio (Piaggio) 
Model P180 airplanes. The proposed action would require repetitively 
inspecting for cracks around the vertical pin and the torque tube 
bottom flange of the rudder and the fasteners that connect the torque 
tube to the bottom flange. If cracks are evident, the proposed action 
would require modifying the rudder torque tube bottom flange assembly 
by replacing the cracked part with a part of improved design which 
would terminate the repetitive inspection. The proposed AD is the 
result of several reports of fatigue cracks around the pin that 
vertically supports the rudder axle. The actions specified by the 
proposed AD are intended to prevent fatigue cracks in the rudder torque 
tube bottom flange which could result in loss of rudder control and 
possible loss of the airplane.

DATES: Comments must be received on or before April 30, 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-56-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. Tom Rodriguez, Program Officer, 
Brussels Aircraft Certification Division, 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. Roman T. 
Gabrys, 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:

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

[[Page 8197]]

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 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-56-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-56-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 certain Piaggio P180 airplanes. The RAI reports that 
fatigue cracks are appearing in the area of the vertical pin support 
and around the torque tube bottom flange of the rudder. These cracks 
were discovered during routine inspections on high flight hour Piaggio 
P180 airplanes. This condition, if not detected and corrected, could 
result in loss of rudder control and possible loss of the airplane.

Relevant Service Information

    Piaggio has issued Service Bulletin 80-0076, ORIGINAL ISSUE: May 
30, 1995 which specifies procedures for inspecting for cracks and 
modifying the torque tube bottom flange and fasteners, if cracks are 
found.
    The RAI classified this service bulletin as mandatory and issued AD 
No. 95-183, Issued July 3, 1995, in order to assure the continued 
airworthiness of these airplanes in Italy.

The FAA's Determination

    This airplane model is manufactured in Italy and is type 
certificated for operation in the United States under the provisions of 
section 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 Piaggio P180 airplanes of the same type 
design registered in the United States, the proposed AD would require 
inspecting for cracks around the torque tube bottom flange, the 
fasteners, and vertical support pin of the rudder; and, if cracks are 
found, modifying the rudder torque tube bottom flange assembly by 
replacing the cracked part with a part of improved design. If no cracks 
are found, the proposed action would require repetitively inspecting 
the area until cracks appear and then modifying the rudder torque tube 
bottom flange by replacing the cracked part with a part of improved 
design. Accomplishment of the proposed modification would be in 
accordance with Piaggio Service Bulletin 80-0076, ORIGINAL ISSUE: May 
30, 1995.

Differences Between the Proposed AD, Service Bulletin, and RAI AD

    I.A.M. Rinaldo Piaggio SB 80-0076, Original Issue May 30, 1995, and 
the RAI AD No. 95-183, dated July 3, 1995, specify repetitively 
inspecting every 500 hours time-in-service (TIS) using a dye penetrant 
method, and if the crack lengths are greater than 6 mm, the part must 
be replaced prior to further flight. If the crack lengths are greater 
than 3 mm, but less than 6 mm, the part must be replaced within the 
next 50 hours TIS; and, if the cracks are less than 3 mm, then the 
parts must be replaced within the next 100 hours TIS. The proposed AD, 
if adopted, would not allow any continued flight with any crack found. 
FAA policy is to disallow airplane operation when known cracks exist in 
primary structure (the rudder is considered primary structure).

Cost Impact

    The FAA estimates that 4 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 6 
workhours per airplane to accomplish the proposed initial inspection 
and that the average labor rate is approximately $60 an hour. Parts are 
not accounted for in this cost analysis because, on some airplanes, 
cracks may never be discovered during one of these inspections. Based 
on these figures, the total cost impact of the proposed AD on U.S. 
operators is estimated to be $1,440 ($360 per airplane). The FAA is not 
taking into account the cost for the repetitive inspections because 
there is no way to determine the number of repetitive inspections that 
might be incurred over the life of the airplane.

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:

[[Page 8198]]

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding a new airworthiness directive 
(AD) to read as follows:

I.A.M. Rinaldo Piaggio: Docket No. 96-CE-56-AD.

    Applicability: Model P180 airplanes (all serial numbers), 
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 (f) 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) after the effective date of this AD, and thereafter as 
indicated in the body of this AD, unless already accomplished.
    To prevent fatigue cracks in the rudder torque tube bottom 
flange which could result in loss of rudder control and possible 
loss of the airplane, accomplish the following:
    (a) Inspect the area around the torque tube, bottom flange, and 
vertical support pin of the rudder for cracks (using a dye penetrant 
method) and visually inspect for cracks in the fasteners that 
connect the torque tube to the bottom flange.

    Note 2: The inspection in Part A of the Compliance section of 
Piaggio Service Bulletin (SB) 80-0076, ORIGINAL ISSUE: May 30, 1995, 
uses different criteria than the inspection required in paragraph 
(a) of this AD. This AD takes precedence over Piaggio SB 80-0076.

    (b) If cracks are found, prior to further flight, modify the 
rudder torque tube bottom flange by replacing any cracked part with 
a part of improved design in accordance with Part B and Attachment 
#1 of the ACCOMPLISHMENT INSTRUCTIONS of Piaggio SB 80-0076, 
ORIGINAL ISSUE: May 30, 1995.
    (c) If no cracks are found, continue to inspect at intervals not 
to exceed 100 hours TIS thereafter until cracks appear. If cracks 
appear during any inspection required by this AD, prior to further 
flight, modify the rudder torque tube bottom flange by the replacing 
cracked part with a part of improved design in accordance with Part 
B and Attachment #1 of the ACCOMPLISHMENT INSTRUCTIONS of Piaggio SB 
80-0076, ORIGINAL ISSUE: May 30, 1995.
    (d) Modifying the rudder torque tube flange by replacing a 
cracked torque tube bottom flange, part number (P/N) 80-373108-103, 
with an improved torque tube bottom flange (P/N 80-373201-001) is 
considered a terminating action for the repetitive inspections 
required in paragraph (c) of this AD.
    (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.
    (f) 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, Brussels Aircraft 
Certification Division, FAA, Europe, Africa, and Middle East Office, 
c/o American Embassy, B-1000 Brussels, Belgium; or the Manager, 
Small Airplane Directorate, Aircraft 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 Division or Manager, Small Airplane 
Directorate.

    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 or the 
Small Airplane Directorate.

    (g) 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 14, 1997.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-4371 Filed 2-21-97; 8:45 am]
BILLING CODE 4910-13-U