[Federal Register Volume 61, Number 110 (Thursday, June 6, 1996)]
[Rules and Regulations]
[Pages 28732-28733]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-14174]



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


DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 90-CE-60-AD; Amendment 39-9654; AD 96-12-12]
RIN 2120-AA64


Airworthiness Directives; The New Piper Aircraft, Inc. (formerly 
Piper Aircraft Corporation) Models PA31, PA31-300, PA31-325, and PA31-
350 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule

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

SUMMARY: This amendment supersedes Airworthiness Directive (AD) 80-22-
04, which currently requires the following on The New Piper Aircraft, 
Inc. (Piper) Models PA31, PA31-300, PA31-325, and PA31-350 airplanes: 
repetitively inspecting the upper section of Fuselage Station (FS) 
317.75 bulkhead for cracks, and incorporating a certain reinforcement 
kit if any crack is found. This action requires inspecting (one-time) 
the upper section of the FS 317.75 bulkhead for cracks, and 
incorporating one of two reinforcement kits depending on whether cracks 
are found in the FS 317.75 bulkhead area. Cracks found on airplanes in 
compliance with the inspection requirements of AD 80-22-04 and the 
Federal Aviation Administration's policy on aging commuter-class 
aircraft prompted this action. The actions specified in this AD are 
intended to prevent structural failure of the vertical fin forward spar 
caused by cracks in the FS 317.75 bulkhead, which, if not detected and 
corrected, could result in loss of control of the airplane.

DATES: Effective July 16, 1996.

    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of July 16, 1996.

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 
Assistant Chief Counsel, Attention: Rules Docket 90-CE-60-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: Christina Marsh, Aerospace Engineer, 
FAA, Atlanta Aircraft Certification Office, Campus Building, 1701 
Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748; 
telephone (404) 305-7362; facsimile (404) 305-7348.

SUPPLEMENTARY INFORMATION:

Events Leading to the AD

    A proposal to amend part 39 of the Federal Aviation Regulations (14 
CFR part 39) to include an AD that would apply to Piper Models PA31, 
PA31-300, PA31- 325, and PA31-350 airplanes was published in the 
Federal Register on January 31, 1996 (61 FR 3338). The action proposed 
to supersede AD 80-22-04 with a new AD that would require inspecting 
(one-time) the upper section of the FS 317.75 bulkhead for cracks in 
accordance with Piper Service Bulletin No. 636A, dated August 26, 1980, 
and accomplishing one of the following, as applicable:

--If any crack is found, incorporating Piper Kit 764-028 in accordance 
with the instructions to that kit, revised June 18, 1990; or
--If no crack is found, incorporating Piper Kit 763-917 in accordance 
with the instructions to that kit, revised June 18, 1990.

    Cracks found on airplanes in compliance with the inspection 
requirements of AD 80-22-04 prompted the proposal.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the

[[Page 28733]]

proposed rule or the FAA's determination of the cost to the public.
    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 2,810 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 12 workhours 
(average of 8 workhours for Kit 763-917 and 16 workhours for Kit 764-
028) per airplane to accomplish the required installation, and that the 
average labor rate is approximately $60 an hour. Parts cost 
approximately $300 per airplane. Based on these figures, the total cost 
impact of this AD on U.S. operators is estimated to be $2,866,200 or 
$1,020 per airplane. This figure is based on the assumption that no 
affected airplane owner/operator has accomplished the required 
installation.
    Piper has informed the FAA that bulkhead reinforcement kits have 
been distributed to equip at least 15 of the affected airplanes. 
Assuming that each of the kits has been incorporated on an affected 
airplane, the cost impact of this AD upon U.S. owners/operators of the 
affected airplanes will be reduced by $15,300 from $2,866,200 to 
$2,850,900.

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 USC 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Airworthiness Directive 
(AD) 80-22-04, Amendment 39-3943, and by adding a new AD to read as 
follows:

96-12-12 The New Piper Aircraft, Inc. (formerly Piper Aircraft 
Corporation): Amendment 39-9654; Docket No. 90-CE-60-AD. Supersedes 
AD 80-22-04, Amendment 39-3943.
    Applicability: The following model and serial number airplanes, 
certificated in any category, that do not have either Piper Kit 764-
028 or Piper Kit 763-917 incorporated at the Fuselage Station (FS) 
317.75 bulkhead area:

------------------------------------------------------------------------
                  Models                             Serial Nos.        
------------------------------------------------------------------------
PA31, PA31-300, and PA31-325..............  31-2 through 31-7912039.    
PA31-350..................................  31-5001 through 31-7952071. 
------------------------------------------------------------------------

    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 within the next 100 hours time-in-service 
after the effective date of this AD, unless already accomplished.
    To prevent structural failure of the vertical fin forward spar 
caused by cracks in the FS 317.75 bulkhead, which, if not detected 
and corrected, could result in loss of control of the airplane, 
accomplish the following:
    (a) Inspect the upper section of the FS 317.75 bulkhead for 
cracks in accordance with the INSTRUCTIONS section of Piper Service 
Bulletin No. 636A, dated August 26, 1980.
    (1) If any crack is found, prior to further flight, incorporate 
Piper Kit 764-028 in accordance with the instructions included with 
that kit, revised June 18, 1990.
    (2) If no crack is found, prior to further flight, incorporate 
Piper Kit 763-917 in accordance with the instructions included with 
that kit, revised June 18, 1980.
    (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), Campus Building, 1701 Columbia Avenue, suite 2-160, College 
Park, Georgia 30337-2748. 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.
    Note 3: Alternative methods of compliance approved in accordance 
with AD 80-22-04 (superseded by this action) are not considered 
approved as alternative methods of compliance with this AD.
    (d) The inspection required by this AD shall be done in 
accordance with Piper Service Bulletin No. 636A, dated August 26, 
1980. The installation required by this AD shall be done in 
accordance with the instructions to Piper Kit 764-028, revised June 
18, 1990, or Piper Kit 763-917, revised June 18, 1990, as 
applicable. 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 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., suite 700, Washington, DC.
    (e) This amendment (39-9654) supersedes AD 80-22-04, Amendment 
39-3943.
    (f) This amendment (39-9654) becomes effective on July 16, 1996. 
Issued in Kansas City, Missouri, on May 30, 1996.
John R. Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-14174 Filed 6-5-96; 8:45 am]
BILLING CODE 4910-13-U