[Federal Register Volume 59, Number 122 (Monday, June 27, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-15380]
[[Page Unknown]]
[Federal Register: June 27, 1994]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 93-CE-60-AD; Amendment 39-8951; AD 94-13-10]
Airworthiness Directives: Piper Aircraft Corporation PA24, PA30,
and PA39 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes Airworthiness Directive (AD) 74-13-
01, which currently requires inspecting (one-time) the stabilator
torque tube bearing support fittings for looseness on certain Piper
Aircraft Corporation (Piper) PA24, PA30, and PA39 series airplanes,
and, if looseness is found, incorporating Piper Part No. 760 835 (Hi-
Shear Rivet Replacement Kit). This action retains the initial
inspection of the stabilator torque tube bearing support fittings, and
makes these inspections repetitive unless the above referenced service
kit is incorporated. Incidents of looseness of the stabilator torque
tube bearing support fittings on several of the affected airplanes in
compliance with the current AD prompted this action. The actions
specified by this AD are intended to prevent loss of pitch control
because of looseness of the stabilator torque tube bearing support
fittings, which could result in loss of control of the airplane.
EFFECTIVE DATE: August 12, 1994.
ADDRESSES: Service information that applies to this AD may be obtained
from the Piper Aircraft Corporation, 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, 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, 1669 Phoenix Parkway, Suite
210C, Atlanta, Georgia 30349; telephone (404) 991-2910; facsimile (404)
991-3606.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that would apply
to certain PA24, PA30, and PA39 series airplanes was published in the
Federal Register on Februrary 1, 1994 (59 FR 4605). The action proposed
to supsersede AD 74-13-01, Amendment 39-1870, with a new AD that would
retain the initial inspection of the stabilator torque tube bearing
support fittings, and make these inspections repetitive unless Piper
Part No. 760 835 (Hi-Shear Rivet Replacement Kit) is incorporated.
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.
After careful review of all available information, 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 nor add any additional burden upon the public than was
already proposed.
The FAA estimates that 4,409 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 1 workhour per
airplane to accomplish the required action, and that the average labor
rate is approximately $55 an hour. Based on these figures, the total
cost impact of the AD on U.S. operators is estimated to be $242,495.
This figure does not account for any repetitive inspections that would
be required by this AD. However, incorporating Piper Part No. 760 835
(Hi-Shear Rivet Replacement Kit) on all four stabilator torque tube
bearing support fittings eliminates the need for the repetitive
inspection requirement of this AD. In addition, this kit may have been
incorporated through compliance with AD 75-27-08, Amendment 39-2624.
This AD requires inspecting the rivets of the stabilator torque tube
bearing support fittings, and incorporating the referenced kit if any
rivets are found misaligned. The cost figure presented above is based
on the assumption that none of the owners/operators affected by this AD
have incorporated Piper Part No. 760 835. The FAA anticipates that
numerous owners/operators have incorporated this kit, thereby reducing
the cost impact of the required action.
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, 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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing AD 74-13-01, Amendment 39-
1870, and by adding a new airworthiness directive to read as follows:
94-13-10 Piper Aircraft Corporation: Amendment 39-8951; Docket No.
93-CE-60-AD; Supersedes AD 74-13-01, Amendment 39-1870.
Applicability: The following model and serial number airplanes,
certificated in any category, that have not incorporated Piper Part
No. 760 835 (Hi-Shear Rivet Replacement Kit) on all four stabilator
torque tube bearing support fittings:
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Models Serial Nos.
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PA24-180, PA24-250 and PA24-260......... 24-1 through 24-5047.
PA24-400................................ 26-2 through 26-148.
PA30.................................... 30-1 through 30-2000.
PA39.................................... 39-1 through 39-155.
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Note 1: Piper Part No. 760 835 (Hi-Shear Rivet Replacement Kit),
may have been incorporated through compliance with AD 75-27-08,
Amendment 39-2624. This AD requires inspecting the rivets of the
stabilator torque tube bearing support fittings, and incorporating
the referenced kit if any rivets are found misaligned. Airplanes
incorporating this kit on all four stabilator torque tube bearing
support fittings are not affected by this AD.
Compliance: Required within the next 100 hour time-in-service
(TIS) after the effective date of this AD, unless already
accomplished, and thereafter as indicated.
To prevent loss of pitch control because of looseness of the
stabilator torque tube bearing support fittings, which could result
in loss of control of the airplane, accomplish the following:
(a) Inspect the stabilator torque tube bearing support fittings
for looseness by accomplishing the following:
(1) Remove the tail cone and right rear aft fuselage access
door.
(2) Grasp the stabilator tip and shake the tip from left to
right and up and down.
Note 2: Piper Service Bulletin 411A, dated April 10, 1974,
specifies these same procedures for inspecting the stabilator torque
tube bearing support fittings.
(b) If looseness is found during the inspection specified in
paragraph (a) of this AD, prior to further flight, incorporate Piper
Part No. 760 835 (Hi-Shear Rivet Replacement Kit) on the affected
fitting, and reinstall the tail cone and right rear aft fuselage
access door.
(c) If looseness is not found during the inspection specified in
paragraph (a) of this AD, prior to further flight, reinstall the
tail cone and right rear aft fuselage access door, and reinspect the
stabilator torque tube bearing support fittings for looseness at
intervals not to exceed 100 hours TIS until Piper Part No. 760 835
(Hi-Shear Rivet Replacement Kit) is incorporated on all four
stabilator torque tube bearing support fittings.
(d) Incorporating Piper Part No. 760 835 (Hi-Shear Rivet
Replacement Kit) on all four stabilator torque tube bearing support
fittings is considered terminating action for the inspection
requirement of this AD.
(e) 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.
(f) 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), 1669 Phoenix Parkway, Suite 210C, 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(g) All persons affected by this directive may obtain copies of
the document referred to herein upon request to the Piper Aircraft
Corporation, 2926 Piper Drive, Vero Beach, Florida 32960; or may
examine this document at the FAA, Central Region, Office of the
Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
(h) This amendment (39-8951) supersedes AD 74-13-01, Amendment
39-1870.
(i) This amendment (39-8951) becomes effective on August 12,
1994.
Issued in Kansas City, Missouri, on June 17, 1994.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 94-15380 Filed 6-24-94; 8:45 am]
BILLING CODE 4910-13-U
