[Federal Register Volume 63, Number 162 (Friday, August 21, 1998)]
[Proposed Rules]
[Pages 44818-44819]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-22542]


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 Proposed Rules
                                                 Federal Register
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
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  Federal Register / Vol. 63, No. 162 / Friday, August 21, 1998 / 
Proposed Rules  

[[Page 44818]]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-CE-139-AD]
RIN 2120-AA64


Airworthiness Directives; Aerostar Aircraft Corporation PA-60-600 
and PA-60-700 Series 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 all Aerostar Aircraft Corporation (Aerostar) 
PA-60-600 and PA-60-700 series airplanes. The proposed AD would require 
repetitively inspecting the forward face of each wing's 55-percent 
upper spar cap for cracks above the main landing gear fitting in the 
top of the wheel well, and replacing or repairing any cracked upper 
spar cap. The proposed AD is the result of reports of spanwise cracks 
in the area above the main landing gear attachment on two of the 
affected airplanes. The actions specified by the proposed AD are 
intended to detect and correct fatigue cracking of the wing upper spar 
cap, which could result in structural failure of the wing spar to the 
point of failure with consequent loss of control of the airplane.

DATES: Comments must be received on or before October 13, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Regional Counsel, 
Attention: Rules Docket No. 97-CE-139-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 the Aerostar Aircraft Corporation, 3608 S. Davison Boulevard, 
Spokane, Washington 99224-5799; telephone: (509) 455-8872, facsimile: 
(509) 838-0831. This information also may be examined at the Rules 
Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Mr. Richard N. Simonson, Aerospace 
Engineer, FAA, Aircraft Certification Office, 1601 Lind Avenue, SW, 
Renton, Washington 98055-4056; telephone: (425) 227-2597; facsimile: 
(425) 227-1181.

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 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. 97-CE-139-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 Regional Counsel, Attention: 
Rules Docket No. 97-CE-139-AD, Room 1558, 601 E. 12th Street, Kansas 
City, Missouri 64106.

Discussion

    The FAA has received two reports of spanwise cracks in the area 
above the main landing gear attachment on Aerostar PA-60-600 and PA-60-
700 series airplanes. In particular these cracks are occurring in the 
55-percent upper spar cap area above the main landing gear fitting in 
the top of the wheel well.
    This condition, if not detected and corrected in a timely manner, 
could result in structural failure of the wing spar to the point of 
failure with consequent loss of control of the airplane.

Relevant Service Information

    Aerostar has issued Service Bulletin SB600-132, dated September 3, 
1997, which specifies procedures for inspecting the forward face of 
each wing's 55-percent upper spar cap for cracks above the main landing 
gear fitting in the top of the wheel well.

The FAA's Determination

    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that AD action should be taken to detect and correct fatigue 
cracking of the wing upper spar cap. If not detected and corrected, 
cracking of the wing upper spar cap could result in structural failure 
of the wing spar to the point of failure with consequent loss of 
control of the airplane.

Explanation of the Provisions of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop in other Aerostar Models PA-60-600, PA-60-601, PA-60-
601P, PA-60-602P, and PA-60-700P airplanes of the same type design, the 
FAA is proposing AD action. The proposed AD would require repetitively 
inspecting the forward face of each wing's 55-percent upper spar cap 
for cracks above the main landing gear fitting in the top of the wheel 
well, and replacing or repairing any cracked upper spar cap.
    Accomplishment of the proposed inspections would be required in 
accordance with Aerostar Service Bulletin SB600-132, dated September 3, 
1997. The proposed repair (if necessary) would be required to be 
accomplished in accordance with an FAA-approved

[[Page 44819]]

repair scheme. Accomplishment of the proposed replacement (if 
necessary) would be required in accordance with the applicable 
maintenance manual.

Cost Impact

    The FAA estimates that 600 airplanes in the U.S. registry would be 
affected by the proposed AD, that it would take approximately 2 
workhours per airplane to accomplish the proposed initial inspection, 
and that the average labor rate is approximately $60 an hour. Based on 
these figures, the total cost impact of the initial inspection 
specified in the proposed AD on U.S. operators is estimated to be 
$72,000, or $120 per airplane.
    These figures only take into account the costs of the proposed 
initial inspection and do not take into account the costs of repetitive 
inspections and the costs associated with any repair that would be 
necessary if cracks are found. The FAA has no way of determining the 
number of repetitive inspections an owner/operator will incur over the 
life of the airplane, or the number of airplanes that will need 
replacement or repair.

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:

PART 39--AIRWORTHINESS DIRECTIVES

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

    Authority: 49 U.S.C. 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:

Aerostar Aircraft Corporation: Docket No. 97-CE-139-AD.

    Applicability: All serial numbers of the following airplane 
models, certificated in any category:

PA-60-600 (Aerostar 600)
PA-60-601P (Aerostar 601P)
PA-60-700P (Aerostar 700P)
PA-60-601 (Aerostar 601)
PA-60-602P (Aerostar 602P)

    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 as indicated in the body of this AD, unless 
already accomplished.
    To detect and correct fatigue cracking of the wing upper spar 
cap, which could result in structural failure of the wing spar to 
the point of failure with consequent loss of control of the 
airplane, accomplish the following:
    (a) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, unless already accomplished, and 
thereafter at intervals not to exceed 100 hours TIS, inspect the 
forward face of each wing's 55-percent upper spar cap for cracks 
above the main landing gear fitting in the top of the wheel well. 
Accomplish this inspection in accordance with the INSTRUCTIONS 
section of Aerostar Service Bulletin SB600-132, dated September 3, 
1997. The initial inspection must be accomplished using dye 
penetrant methods and all subsequent inspections must be, at the 
very least, visual inspections.
    (b) If any crack(s) is/are found during any inspection required 
by paragraph (a) of this AD, prior to further flight, accomplish 
either paragraph (b)(1) or (b)(2) of this AD (below):
    (1) Replace the upper spar cap in accordance with the applicable 
maintenance manual, and continue to repetitively inspect as required 
by paragraph (a) of this AD; or
    (2) Obtain a repair scheme from the manufacturer through the 
FAA, Small Airplane Directorate, at the address specified in 
paragraph (d) of this AD; incorporate this scheme; and continue to 
repetitively inspect as required by paragraph (a) of this AD, unless 
specified differently in the instructions to the repair scheme.
    (c) 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.
    (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) All persons affected by this directive may obtain copies of 
the document referred to herein upon request to the Aerostar 
Aircraft Corporation, 3608 S. Davison Boulevard, Spokane, Washington 
99224-5799; or may examine this document at the FAA, Central Region, 
Office of the Regional Counsel, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

    Issued in Kansas City, Missouri, on August 13, 1998.
Michael Gallagher,
Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-22542 Filed 8-20-98; 8:45 am]
BILLING CODE 4910-13-P