[Federal Register Volume 60, Number 221 (Thursday, November 16, 1995)]
[Rules and Regulations]
[Pages 57539-57540]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-28147]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-CE-81-AD; Amendment 39-9431; AD 95-23-11]
Airworthiness Directives; Aerostar Aircraft Corporation PA-60-600
(Aerostar 600) Series (Formerly Piper Aircraft Corporation) Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to certain Aerostar Aircraft Corporation (Aerostar) PA-60-600
series airplanes. This action requires repetitively inspecting the
fuselage horizontal stabilizer attach fittings for cracks, and
replacing any cracked fuselage horizontal stabilizer attach fitting. A
report of several cracks found on the forward horizontal stabilizer
attach spar fitting on an Aerostar Model PA-60-601P airplane prompted
this action. The actions specified by this AD are intended to prevent
undetected cracked fuselage horizontal attach fittings, which could
result in the fuselage horizontal stabilizer separating from the
airplane while in flight with subsequent loss of control of the
airplane.
DATES: Effective November 30, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 30, 1995.
Comments for inclusion in the Rules Docket must be received on or
before January 10, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket 95-CE-81-AD, Room 1558, 601 E. 12th
Street, Kansas City, Missouri 64106.
Service information that applies to this AD may be obtained from
the Aerostar Aircraft Corporation, Customer Service Department, South
3608 Davison Boulevard, Spokane, Washington 99204; telephone (509) 455-
8872. 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-81-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. Richard N. Simonson, Aerospace
Engineer, Seattle Aircraft Certification Office, 1601 Lind Avenue,
S.W., Renton, Washington 98055-4056; telephone (206) 227-2597;
facsimile (206) 227-1181.
SUPPLEMENTARY INFORMATION: The FAA has received a report where several
cracks were found in the fuselage forward horizontal stabilizer attach
spar fitting on an Aerostar Model PA-60-601P airplane. Further
investigation revealed that stress corrosion caused the cracks. This
airplane had been inspected for cracks in the fuselage horizontal
stabilizer attach spar fittings consistently at intervals of 200 hours
time-in-service (TIS).
The affected airplane had a total usage time of 4,279 hours (TIS),
which is considered about average for the fleet of approximately 600
Aerostar PA-60-600 series airplanes registered in the United States.
Undetected cracked fuselage horizontal stabilizer attach fittings could
result in the fuselage horizontal stabilizer separating from the
airplane while in flight with subsequent loss of control of the
airplane.
Aerostar has issued Service Bulletin SB600-130, dated September 26,
1995, which specifies procedures for inspecting fuselage horizontal
stabilizer attach fittings on Aerostar PA-60-600 series airplanes.
After examining the circumstances and reviewing all available
information related to the incidents described above including the
referenced service bulletin, the FAA has determined that AD action
should be taken to prevent undetected cracked fuselage horizontal
attach fittings, which could result in the fuselage horizontal
stabilizer separating from the airplane while in flight with subsequent
loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Aerostar PA-60-600 series airplanes of the
same type design, this AD requires repetitively inspecting the fuselage
horizontal stabilizer attach fittings for cracks, and replacing any
cracked fuselage horizontal stabilizer attach fitting with a
serviceable approved part of like design. Accomplishment of these
inspections are in accordance with Aerostar Service Bulletin SB600-130,
dated September 26, 1995. Any fuselage horizontal stabilizer attach
fitting replacement that is required shall be accomplished in
accordance with the applicable maintenance manual.
The compliance time of this AD is presented in calendar time and
hours TIS. Cracking of the fuselage horizontal stabilizer attach
fittings on the affected airplane is caused by stress corrosion, which
starts as a result of stress loads incurred through operation.
Corrosion can then develop regardless of whether the airplane is in
flight. The cracks may not be noticed initially as a result of the
stress loads, but could then develop through corrosion. In order to
ensure that these stress corrosion cracks do not go undetected, a
compliance time of specific hours TIS and calendar time (whichever
occurs first) is utilized.
Since a situation exists (possible separation of the fuselage
horizontal stabilizer separating from the airplane during flight) that
requires the immediate adoption of this regulation, it is found that
notice and opportunity for public prior comment hereon are
impracticable, and that good cause exists for making this amendment
effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting immediate flight safety and,
[[Page 57540]]
thus, was not preceded by notice and opportunity to comment, comments
are invited on this rule. Interested persons are invited to comment on
this 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 will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD 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. 95-CE-81-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation and that must be issued immediately to correct an unsafe
condition in aircraft, and is not a significant regulatory action under
Executive Order 12866. It has been determined further that this action
involves an emergency regulation under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979). If it is determined that
this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket (otherwise, an evaluation is
not required). A copy of it, if filed, may be obtained from the Rules
Docket.
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), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
95-23-11 Aerostar Aircraft Corporation: Amendment 39-9431; Docket
No. 95-CE-81-AD.
Applicability: The following model and serial number airplanes,
certificated in any category:
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Models Serial Nos.
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PA-60-600............................ 60-0001-003 through
Aerostar 600 60-0933-8161262.
PA-60-601............................ 61-0001-004 through
Aerostar 601 61-0880-8162157.
PA-60-601P........................... 61P-0157-001 through
Aerostar 601P 61P-0860-8163455.
PA-60-602P........................... 62P-0750-8165001
Aerostar 602P through 60-8365021
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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 initially within the next 25 hours time-in-
service (TIS) after the effective date of this AD or within the next
2 calendar months after the effective date of this AD, whichever
occurs first, unless already accomplished, and thereafter at
intervals not to exceed 100 hours TIS or 12 calendar months,
whichever occurs first.
To prevent the fuselage horizontal stabilizer from separating
from the airplane while in flight because of cracked attach
fittings, which, if not detected and replaced, could result in loss
of control of the airplane, accomplish the following:
(a) Inspect the upper and lower horizontal flanges on the left
and right sides of the following parts for cracks in accordance with
the INSTRUCTIONS section of Aerostar Service Bulletin SB600-130,
dated September 26, 1995.
(1) The part number (P/N) 210006-001 fitting (forward fuselage
horizontal stabilizer attach fitting); and
(2) The P/N 210007-001 fitting (aft fuselage horizontal
stabilizer attach fitting).
(b) Prior to further flight, replace any fuselage horizontal
stabilizer attach fitting found cracked during any inspection
required by paragraph (a) of this AD. Accomplish this replacement in
accordance with the applicable maintenance manual.
(c) Special flight permits may be issued in accordance with
Secs. 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
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, Seattle Aircraft
Certification Office (ACO), 1601 Lind Avenue, SW., Renton,
Washington 98055-4056. The request shall be forwarded through an
appropriate FAA Maintenance Inspector, who may add comments and then
send it to the Manager, Seattle ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Seattle ACO.
(e) The inspections required by this AD shall be done in
accordance with Aerostar Service Bulletin SB600-130, dated September
26, 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 the Aerostar Aircraft
Corporation, Customer Service Department, South 3608 Davison
Boulevard, Spokane, Washington 99204. 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., 7th Floor,
suite 700, Washington, DC.
(f) This amendment (39-9431) becomes effective on November 30,
1995.
Issued in Kansas City, Missouri, on November 8, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-28147 Filed 11-15-95; 8:45 am]
BILLING CODE 4910-13-U
