[Federal Register Volume 63, Number 227 (Wednesday, November 25, 1998)]
[Rules and Regulations]
[Pages 65056-65057]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-31435]
[[Page 65056]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-139-AD; Amendment 39-10916; AD 98-24-29]
RIN 2120-AA64
Airworthiness Directives; Aerostar Aircraft Corporation PA-60-600
and PA-60-700 Series 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 all Aerostar Aircraft Corporation (Aerostar) PA-60-600 and
PA-60-700 series airplanes. This AD requires 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. Reports of spanwise
cracks in the area above the main landing gear attachment on two of the
affected airplanes prompted this action. The actions specified by this
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: Effective January 8, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 8, 1999.
ADDRESSES: Service information that applies to this AD may be obtained
from the Aerostar Aircraft Corporation, 10555 Airport Drive, Coeur
d'Alene Airport, Hayden Lake, Idaho 83835-9742; telephone: (208) 762-
0338. This information may also be examined at 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; 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, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue,
SW, Renton, Washington 98055-4056; telephone: (425) 227-2597;
facsimile: (425) 227-1181.
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 all Aerostar PA-60-
600 and PA-60-700 series airplanes was published in the Federal
Register as a notice of proposed rulemaking (NPRM) on August 21, 1998
(63 FR 44818). The NPRM proposed to 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 as specified in the NPRM
would be required in accordance with Aerostar Service Bulletin SB600-
132, dated September 3, 1997. Accomplishment of the proposed repair (if
necessary) would be required in accordance with an FAA-approved repair
scheme. Accomplishment of the proposed replacement (if necessary) would
be required in accordance with the applicable maintenance manual.
The NPRM was the result of reports of spanwise cracks in the area
above the main landing gear attachment on two of the affected
airplanes.
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 related to the
subject presented above, the FAA has determined that air safety and the
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.
Cost Impact
The FAA estimates that 600 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 2 workhours per
airplane to accomplish the 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 this 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 initial
inspection and do not take into account the costs of repetitive
inspections and the costs associated with any repair that will 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 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 U.S.C. 106(g), 40113, 44701.
[[Page 65057]]
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
98-24-29 Aerostar Aircraft Corporation: Amendment 39-10916; 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-60-601 (Aerostar 601)
PA-60-601P (Aerostar 601P)
PA-60-602P (Aerostar 602P)
PA-60-700P (Aerostar 700P)
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
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 SB600-132, dated September
3, 1997. 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, 10555 Airport Drive, Coeur d'Alene Airport, Hayden
Lake, Idaho 83835-9742. Copies may be inspected at the FAA, Central
Region, Office of the Regional 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.
(f) This amendment becomes effective on January 8, 1999.
Issued in Kansas City, Missouri, on November 17, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 98-31435 Filed 11-24-98; 8:45 am]
BILLING CODE 4910-13-U
