[Federal Register Volume 61, Number 81 (Thursday, April 25, 1996)]
[Proposed Rules]
[Pages 18299-18303]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10167]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-09-AD]
RIN 2120-AA64
Airworthiness Directives; The New Piper Aircraft, Inc. PA24,
PA28R, PA30, PA32R, PA34, and PA39 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to supersede AD 95-20-07, which
currently requires repetitively inspecting the main gear side brace
studs for cracks on certain The New Piper Aircraft, Inc. (Piper) PA24,
PA28R, PA30, PA32R, PA34, and PA39 series airplanes, and replacing any
cracked main gear side brace stud. The proposed action would retain the
repetitive inspection and possible replacement requirements of AD 95-
20-07, would remove airplanes with a certain main gear side brace
assembly configuration from the ``Applicability'' section of the
current AD, and would incorporate additional modification and
replacement options. Additional information on the design and service
history of the affected airplanes concerning this subject received by
the Federal Aviation Administration (FAA) after issuance of AD 95-20-07
prompted the proposed action. The actions specified by the proposed AD
are intended to prevent a main landing gear collapse caused by main
gear side brace stud cracks, which, if not detected and corrected,
could result in loss of control of the airplane during landing
operations.
DATES: Comments must be received on or before June 25, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-CE-09-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.
Information that applies to the proposed AD may be examined at the
Rules Docket at the address above.
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:
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. 96-CE-09-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 Assistant Chief Counsel,
Attention: Rules Docket No. 96-CE-09-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
AD 95-20-07, Amendment 39-9386 (60 FR 52073, October 5, 1995),
currently requires repetitively inspecting (using liquid penetrant or
magnetic particle methods) the main gear side brace studs for cracks on
certain Piper PA24, PA28R, PA30, PA32R, PA34, and PA39 series
airplanes, and replacing any cracked main gear side brace stud. A minor
correction on this action that specified who could accomplish the
inspection was published in the Federal Register on November 15, 1995
(60 FR 57333).
The FAA has re-examined all available information related to AD 95-
20-07, including additional information received from The New Piper
Aircraft, Inc., and owners/operators of the affected airplanes. From
this examination, the FAA has determined the following:
--That a third main gear side brace assembly containing the \5/8\-inch
stud, part number (P/N) 78717-02, with a two-piece bushing, P/N 67026-
09, was installed (at manufacture) on Piper Model PA34-200T, serial
numbers 34-7670325 through 34-7770372. AD 95-20-07 should not apply to
these airplanes with this main gear side brace assembly configuration;
and
--That Piper PA28R, PA32R, and PA34 series airplane owners/operators
should have the option of incorporating a modification that would
eliminate the repetitive inspection requirement of AD 95-20-07. This
modification consists of reaming the existing two-piece bushings, P/N
67026-6, to an inside diameter of .624-inch to .625-inch, rechamfering
the bushings, and installing the \5/8\-inch stud, P/N 78717-02. The
owner/operator would have the choice of incorporating this
modification, installing a P/N 95643-06/-07/-08/-09 main gear side
brace bracket assembly, or continuing to reinspect the main gear side
brace assembly.
Based upon the information described above, the FAA has determined
that AD action should be taken to prevent a main landing gear collapse
caused by main gear side brace stud cracks, which, if not detected and
corrected, could result in loss of control of the airplane during
landing operations.
Since an unsafe condition has been identified that is likely to
exist or
[[Page 18300]]
develop in other Piper PA24, PA28R, PA30, PA32R, PA34, and PA39 series
airplanes of the same type design, the proposed AD would supersede AD
95-20-07 with a new AD that would (1) retain the requirement of
repetitively inspecting the main gear side brace assembly, and
replacing any cracked main gear side brace stud. This includes the
inspection-terminating replacement contained in AD 95-20-07; (2) remove
from the ``Applicability'' section of the current AD the Piper Model
PA34-200T airplanes that incorporate a main gear side brace assembly
containing the \5/8\-inch stud, part number (P/N) 78717-02, with a two-
piece bushing, P/N 67026-09; and (3) incorporate, as an option, an
inspection-terminating modification for Piper PA28R, PA32R, and PA34
airplanes. This modification consists of reaming the existing two-piece
bushings, P/N 67026-6, to an inside diameter of .624-inch to .625-inch,
rechamfering the bushings, and installing the \5/8\-inch stud, P/N
78717-02.
The FAA estimates that 13,200 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximately 5
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Based on these
figures, the total cost impact of the proposed inspection on U.S.
operators is estimated to be $3,960,000. This figure represents the
total cost of the proposed initial inspection, and does not reflect
costs for any of the proposed repetitive inspections or possible
replacements. The FAA has no way of determining how many main gear side
brace studs may need replacement or how many repetitive inspections
each owner/operator may incur over the life of the airplane.
In addition, the proposed AD would require the same inspections
required by AD 95-20-07. The only difference between the proposed AD
and AD 95-20-07 is the addition of an inspection-terminating
modification option and the elimination from the ``Applicability''
section certain airplanes that incorporate a certain main side brace
stud assembly. The proposed AD would not provide any additional cost
impacts over that already required by AD 95-20-07.
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 14
CFR part 39 of the Federal Aviation Regulations 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) 95-20-07, Amendment 39-9386, and by adding a new AD to read as
follows:
The New Piper Aircraft, Inc.: Docket No. 96-CE-09-AD; Supersedes AD
95-20-07, Amendment 39-9386.
Applicability: The following airplane models and serial numbers,
certificated in any category:
1. All serial numbers of Models PA24, PA24-250, PA24-260, PA24-
400, PA30, and PA39 airplanes;
2. The following model and serial number airplanes that are not
equipped with a part number (P/N) 78717-02 main landing gear side
brace stud in both right and left main landing gear sidebrace
bracket assemblies:
------------------------------------------------------------------------
Model Serial No.
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PA28R-180 28R-30002 through 28R-31135, and 28R-
7130001 through 28R-7130013.
PA28R-200 28R-35001 through 28R-35820, and 28R-
7135001 through 28R-7635539.
PA28R-201 28R-7737002 through 28R-7737096.
PA28R-201T 28R-7703001 through 28R-7703239.
PA32R-300 32R-7680001 through 32R-7780444.
PA34-200 All serial numbers.
PA34-200T 34-7570001 through 34-7770372.
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Note 1: P/N 78717-02 side brace stud was installed at
manufacture on Piper Model PA34-200T airplanes, serial numbers 34-
7670325 through 34-7770372.
Note 2: 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 (e) 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 initially as follows, and thereafter as
specified in the body of this AD:
1. For the affected Models PA28R-180, PA28R-200, PA28R-201,
PA28R-201T, PA32R-300, PA34-200, and PA34-200T airplanes: Within the
next 100 hours time-in-service (TIS) after the effective date of
this AD or, if the main gear side brace stud has already been
inspected or replaced as specified in this AD, within 500 hours TIS
after the last inspection or replacement, whichever occurs later.
2. For the affected Models PA24, PA24-250, PA24-260, PA24-400,
PA30, and PA39 airplanes: Within the next 100 hours time-in-service
(TIS) after the effective date of this AD or, if the main gear side
brace stud has already been inspected or replaced as specified in
this AD, within 1,000 hours TIS after the last inspection or
replacement, whichever occurs later.
To prevent main landing gear (MLG) collapse caused by main gear
side brace stud cracks, which, if not detected and corrected, could
result in loss of control of the airplane during landing operations,
accomplish the following:
Note 3: The paragraph structure of this AD is as follows:
Level 1: (a), (b), (c), etc.
Level 2: (1), (2), (3), etc.
Level 3: (i), (ii), (iii), etc.
Level 2 and Level 3 structures are designations of the Level 1
paragraph they immediately follow.
(a) Remove both the left and right main gear side brace studs
from the airplane in accordance with the instructions contained in
the Landing Gear section of the maintenance manual, and inspect each
main gear side brace stud for cracks, using Type I (fluorescent)
liquid penetrant or magnetic particle inspection methods. Figure 1
of this
[[Page 18301]]
AD depicts the area of the sidebrace stud shank where the sidebrace
stud is to be inspected.
Note 4: All affected Models PA24 and PA24-250 airplanes were
equipped at manufacture with P/N 20829-00 main gear side brace
studs. All affected Models PA24-260, PA24-400, PA30, and PA39
airplanes were equipped at manufacture with P/N 22512-00 main gear
side brace studs. The Appendix included with this AD contains
information on determining the P/N of the bracket assembly on the
affected PA28R, PA32R, and PA34 series airplanes.
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[GRAPHIC] [TIFF OMITTED] TP25AP96.004
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(1) For any main gear side brace stud found cracked, prior to
further flight, replace the cracked stud with an FAA-approved
serviceable part (part numbers referenced in the table in paragraph
(b) of this AD or FAA-approved equivalent) in accordance with the
instructions contained in the Landing Gear section of the applicable
maintenance manual, and accomplish one of the following, as
applicable:
(i) Reinspect and replace (as necessary) as specified in
paragraph (b) of this AD; or
(ii) For the affected Models PA28R-180, PA28R-200, PA28R-201,
PA28R-201T, PA32R-300, PA34-200, and PA34-200T airplanes, the P/N
95299-00 or 95299-02 main gear side brace studs are no longer
manufactured. Install a new main gear side brace stud bracket
assembly, P/N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09,
as applicable. No repetitive inspections will be required by this AD
for these affected airplane models when this bracket assembly is
installed; or
(iii) For the affected Models PA28R-180, PA28R-200, PA28R-201,
PA28R-201T, PA32R-300, PA34-200, and PA34-200T airplanes, ream the
existing two-piece bushings, P/N 67026-6, to an inside diameter of
.624-inch to .625-inch, rechamfer the bushings, and install the \5/
8\-inch stud, P/N 78717-02. No repetitive inspections will be
required by this AD when this action is accomplished. If the
bushings cannot be reamed while installed in the bracket (i.e., the
brackets are loose), then install a main gear side brace bracket
assembly, P/N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09,
as applicable. No repetitive inspections will be required by this AD
when this bracket assembly is installed.
(2) For any main gear side brace stud not found cracked, prior
to further flight, reinstall the uncracked stud in accordance with
the instructions contained in the Landing Gear section of the
applicable maintenance manual, and reinspect and replace (as
necessary) as specified in paragraph (b) of this AD.
(b) Reinspect both the left and right main gear side brace
studs, using Type I (fluorescent) liquid penetrant or magnetic
particle inspection methods. Replace any cracked stud or reinstall
any uncracked stud as specified in paragraphs (a)(1) and (a)(2) of
this AD, respectively:
------------------------------------------------------------------------
TIS inspection
Part No. installed interval Model airplanes installed
(hours) on
------------------------------------------------------------------------
20829-00.................... 1,000 PA24 and PA24-250.
22512-00.................... 1,000 PA24-260, PA24-400, PA30,
and PA39.
95299-00 or 95299-02........ 500 PA28R-180, PA28R-200,
PA28R-201, PA28R-201T,
PA32R-300, PA34-200, and
PA34-200T.
------------------------------------------------------------------------
Note 5: Accomplishing the actions of this AD does not affect the
requirements of AD 77-13-21, Amendment 39-3093. The tolerance
inspection requirements of that AD still apply for Piper PA24, PA30,
and PA39 series airplanes.
(c) Owners/operators of the affected Models PA28R-180, PA28R-
200, PA28R-201, PA28R-201T, PA32R-300, PA34-200, and PA34-200T
airplanes may accomplish one of the following at any time to
terminate the repetitive inspection requirement of this AD:
(1) Install a main gear side brace bracket assembly, P/N 95643-
06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, as applicable,
which contains the \5/8\-inch diameter main gear side brace stud, P/
N 78717-02, and the one-piece bushing, P/N 67026-12; or
(2) Ream the existing two-piece bushings, P/N 67026-6, to an
inside diameter of .624-inch to .625-inch, rechamfer the bushings,
and install the \5/8\-inch stud, P/N 78717-02. If the bushings
cannot be reamed while installed in the bracket (i.e., the brackets
are loose), then install a main gear side brace bracket assembly, P/
N 95643-06, P/N 95643-07, P/N 95643-08, or P/N 95643-09, as
applicable.
(d) 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.
(e) 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, 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 6: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(f) Alternative methods of compliance approved in accordance
with AD 95-20-07, Amendment 39-9386, are considered approved as
alternative methods of compliance with this AD.
(g) Information related to this AD may be inspected at the FAA,
Central Region, Office of the Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri.
(h) This amendment supersedes AD 95-20-07, Amendment 39-9386.
Appendix to Docket No. 96-CE-09-AD--Information To Determine Main Gear
Side Brace Stud Assembly Part Number (P/N)
--The P/N 95643-00/-01/-02/-03 bracket assembly contains the 9/16-
inch diameter main gear side brace stud, P/N 95299-00/-02, and a
two-piece bushing, P/N 67026-6.
--The P/N 95643-06/-07/-08/-09 bracket assembly contains the 5/8-
inch diameter main gear side brace stud, P/N 78717-02, and a one-
piece bushing, P/N 67026-12.
--Both the one-piece and the two-piece bushing have a visible
portion of the bushing flange, i.e., bushing shoulder.
--Whether a one-piece or two-piece bushing is installed may be
determined by measuring the outside diameter of the bushing flange
with a micrometer (jaws of the caliper must be 3/32-inch or less).
The two-piece bushing will have an outside diameter of 1.00 inch and
the one-piece bushing will have an outside diameter of 1.128 to
1.130 inches.
--The one-piece bushing contains a visible chamfer in the center of
the bushing, and the chamfer in the two-piece bushing is not visible
when the stud is installed.
--If P/N 95643-00/-01/-02/-03 bracket assembly is installed or the
above information cannot be utilized, the main gear side brace stud
will need to be removed from the bracket to determine the shank
diameter and main gear side brace stud P/N.
--P/N 95299-00 and P/N 95299-02 main gear side brace studs are 9/16-
inch in diameter.
--P/N 95643-00/-01/-02/-03 bracket assembly may have been modified
to accommodate the 5/8-inch diameter main gear side brace stud, P/N
78717-02.
Issued in Kansas City, Missouri, on April 19, 1996.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-10167 Filed 4-24-96; 8:45 am]
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