[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
