[Federal Register Volume 63, Number 81 (Tuesday, April 28, 1998)]
[Rules and Regulations]
[Pages 23205-23206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11161]
[[Page 23205]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-CE-48-AD; Amendment 39-10506; AD 98-09-25]
RIN 2120-AA64
Airworthiness Directives; The New Piper Aircraft, Inc. Models PA-
31, PA-31-300, PA-31-325, and PA-31-350 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 certain The New Piper Aircraft, Inc. (Piper) Models PA-31,
PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD requires
replacing the lower spar splice plate and reworking the lower spar
caps. This AD results from numerous reports of fretting and cracking of
the lower spar splice plates on Piper PA-31 series airplanes in
Australia, and a report of one incident in the United States. The
actions specified by this AD are intended to prevent failure of the
lower spar splice plate caused by fretting and cracking, which could
result in loss of control of the airplane.
DATES: Effective June 15, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 15, 1998.
ADDRESSES: Service information that applies to this AD may be obtained
from The New Piper Aircraft, Inc., Customer Services, 2926 Piper Drive,
Vero Beach, Florida 32960. 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-48-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. William O. Herderich, Aerospace
Engineer, FAA, Atlanta Aircraft Certification Office, 1895 Phoenix
Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770) 703-
6084; facsimile: (770) 703-6097.
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 certain Piper Models
PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes was published in
the Federal Register as a notice of proposed rulemaking (NPRM) on
August 22, 1997 (62 FR 44597). The NPRM proposed to require replacing
the lower spar splice plate and reworking the lower spar caps.
Accomplishment of the proposed action as specified in the NPRM would be
required in accordance with Piper Main Spar Splice Plate Replacement
(Lower) Kit No. 766-641, Drawing 88255, Revision A, dated May 12, 1997;
or Piper Main Spar Splice Plate Replacement (Lower) Kit No. 766-640,
Drawing 88254, Revision A, dated May 12, 1997.
The NPRM was the result of numerous reports of fretting and
cracking of the lower spar splice plates on Piper PA-31 series
airplanes in Australia, and a report of one incident in the United
States.
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 has received data from the Australian Civil Aviation Safety
Authority (CASA), which was based on the analysis of 34 airplanes. This
data shows the lower spar splice plate replacement threshold as the
following:
--6,000 hours time-in-service (TIS) for Models PA-31, PA-31-300, and
PA-31-325 airplanes; and
--13,000 hours TIS for Model PA-31-350 airplanes
The lower spar splice plate replacement threshold was presented as
2,500 hours TIS in the NPRM. The FAA conducted statistical analysis on
this data received from the Australian CASA. This analysis shows that
the thresholds presented by the Australian CASA are reliable and
accurate.
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
the change in the compliance time (from 2,500 hours TIS to 6,000 hours
TIS or 13,000 hours TIS, as applicable) and 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 1,700 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 8 workhours per
airplane to accomplish this replacement, and that the average labor
rate is approximately $60 an hour. Parts cost approximately $210 per
airplane. Based on these figures, the total cost impact of this AD on
U.S. operators is estimated to be $1,173,000, or $690 per airplane.
Piper has informed the FAA that, as of August 22, 1997 (the
publication date of the NPRM), parts have been distributed to equip 1
affected airplane. Presuming that this set of parts is installed on an
affected airplane, the cost impact of this AD will be reduced by $690,
from $1,173,000 to $1,172,310.
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:
[[Page 23206]]
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:
98-09-25 The New Piper Aircraft, Inc.: Amendment 39-10506; Docket
No. 97-CE-48-AD.
Applicability: The following airplane model and serial numbers,
certificated in any category:
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Models Serial numbers
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PA-31, PA-31-300, and PA-31-325........... 31-2 through 31-8312019.
PA-31-350................................. 31-5001 through 31-8553002.
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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 (c) 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 follows, unless already accomplished:
1. For the affected Models PA-31, PA-31-300, and PA-31-325
airplanes: Upon accumulating 6,000 hours on the lower spar splice
plate or within the next 100 hours time-in-service (TIS) after the
effective date of this AD, whichever occurs later; and
2. For the affected Model PA-31-350 airplanes: Upon accumulating
13,000 hours TIS on the lower spar splice plate or within the next
100 hours TIS after the effective date of this AD, whichever occurs
later.
To prevent failure of the lower spar splice plate caused by
fretting and cracking, which could result in loss of control of the
airplane, accomplish the following:
(a) Replace the lower spar splice plate and rework the lower
spar caps in accordance with the instructions included in the
following kits, as applicable, and as referenced in Piper Service
Bulletin No. 1003, dated June 16, 1997:
(1) Main Spar Splice Plate Replacement (Lower) Kit No. 766-640,
Drawing 88254, Revision A, dated May 12, 1997, which applies to
Models PA-31, PA-31-300, and Piper PA-31-325 airplanes; and
(2) Main Spar Splice Plate Replacement (Lower) Kit No. 766-641,
Drawing 88255, Revision A, dated May 12, 1997, which applies to
Model PA-31-350 airplanes.
(b) 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.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be
approved by the Manager, Atlanta Aircraft Certification Office
(ACO), 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349.
The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Atlanta ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(d) The replacements required by this AD shall be done in
accordance with the instructions to Piper Main Spar Splice Plate
Replacement (Lower) Kit No. 766-641, Drawing 88255, Revision A,
dated May 12, 1997; or Piper Main Spar Splice Plate Replacement
(Lower) Kit No. 766-640, Drawing 88254, Revision A, dated May 12,
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 New Piper Aircraft, Inc.,
2926 Piper Drive, Vero Beach, Florida 32960. 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.
(e) This amendment becomes effective on June 15, 1998.
Issued in Kansas City, Missouri, on April 21, 1998.
Marvin R. Nuss,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-11161 Filed 4-27-98; 8:45 am]
BILLING CODE 4910-13-U
