AD 97-15-14

[Federal Register Volume 62, Number 144 (Monday, July 28, 1997)]
[Rules and Regulations]
[Pages 40264-40266]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-19439]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-CE-56-AD; Amendment 39-10088; AD 97-15-14]
RIN 2120-AA64


Airworthiness Directives; Industrie Aeronautiche e Meccaniche 
Rinaldo Piaggio S.p.A. Model P-180 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to Industrie Aeronautiche e Meccaniche Rinaldo Piaggio S.p.A. 
(Piaggio) Model P-180 airplanes. This action requires 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 (torque tube bottom flange assembly). If cracks are not found, 
repetitively inspect until cracks are visible. If cracks are evident, 
this action requires modifying the rudder torque tube bottom flange 
assembly by replacing the cracked part with a part of improved design, 
which terminates the repetitive inspection. This AD is the result of 
several reports of fatigue cracks around the pin that vertically 
supports the rudder axle. The actions specified by this 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: Effective September 19, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of September 19, 1997.

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 96-CE-56-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. 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:

Events Leading to the Issuance of This AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Piaggio Model P-180 
airplanes was published in the Federal Register on February 24, 1997 
(62 FR 8196). The action proposed to require inspecting for cracks in 
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 assembly (part number 
(P/N) 80-373108-103 or an FAA approved equivalent) by replacing the 
cracked part with a part of improved design (P/N 80-373201-001 or an 
FAA approved equivalent). Accomplishment of the proposed modification 
would be in accordance with Piaggio Service Bulletin (SB) 80-0076, 
ORIGINAL ISSUE: May 30, 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.

The FAA's Determination

    After careful review of all available information, including the 
service information related to the subject presented above, the FAA has 
determined that air safety and the

[[Page 40265]]

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.

Differences Between the 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 FAA has established a policy to disallow airplane operation 
when known cracks exist in primary structure, unless the ability to 
sustain ultimate load with these cracks is proven. The torque tube 
bottom flange, the fasteners, and the vertical support pin in the 
rudder (torque tube bottom flange assembly) are considered primary 
structure, and the FAA has not received any analysis to prove that 
ultimate load can be sustained with cracks in this area. For this 
reason, the FAA has determined that AD action should be taken to 
require replacement of any cracked torque tube bottom flange assembly 
in the rudder.

Cost Impact

    The FAA estimates that 4 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 6 workhours per 
airplane to accomplish the 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 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 will be incurred over the life of 
the airplane.

Regulatory Impact

    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 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:

97-15-14  Industrie Aeronautiche E Meccaniche Rinaldo PIAGGIO S.P.A. 
(PIAGGIO): Amendment No. 39-10088; Docket No. 96-CE-56-AD.

    Applicability: Model P-180 airplanes (all serial numbers), 
certificated in any category.

    Note 1: This AD applies to the 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 the airplane that has been modified, 
altered, or repaired so that the performance of the requirements of 
this AD are affected, the owner/operator must request approval for 
an alternative method of compliance in accordance with paragraph (g) 
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, unless already 
accomplished, and thereafter as indicated in the body of this AD.
    To prevent fatigue cracks in the rudder torque tube bottom 
flange assembly, which could result in loss of rudder control and 
possible loss of the airplane, accomplish the following:
    (a) Inspect the torque tube bottom flange assembly 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 assembly by replacing the 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 assembly by 
replacing the 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 bottom flange assembly by 
replacing torque tube bottom flange assembly with an improved torque 
tube bottom flange assembly as specified in paragraphs (b) and (c) 
of this AD 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, 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, Small Airplane 
Directorate.


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    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Small Airplane Directorate.

    (g) The inspections, modification, and replacement required by 
this AD shall be done in accordance with Piaggio Service Bulletin 
80-0076, ORIGINAL ISSUE: May 30, 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 of this 
service bulletin may be obtained from Industrie Aeronautiche e 
Meccaniche Rinaldo Piaggio S.p.A., Via Ciobrario, 4 16154 Genoa, 
Italy. Copies of this document 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.
    (h) This amendment (39-10088) becomes effective on September 19, 
1997.

    Issued in Kansas City, Missouri, on July 16, 1997.
Carolanne L. Cabrini,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-19439 Filed 7-25-97; 8:45 am]
BILLING CODE 4910-13-U