[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]



=======================================================================
-----------------------------------------------------------------------

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.

-----------------------------------------------------------------------

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:

------------------------------------------------------------------------
                Models                            Serial Nos.           
------------------------------------------------------------------------
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               
------------------------------------------------------------------------

    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