[Federal Register Volume 63, Number 99 (Friday, May 22, 1998)]
[Proposed Rules]
[Pages 28294-28299]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-13656]
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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. PA-24, PA-
28R, PA-30, PA-32R, PA-34, and PA-39 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to revise Airworthiness Directive (AD)
97-01-01, which currently requires repetitively inspecting the main
gear sidebrace studs for cracks on The New Piper Aircraft, Inc. (Piper)
Models PA-24, PA-28R, PA-30, PA-32R, PA-34, and PA-39 series airplanes,
and replacing any main gear sidebrace stud found cracked. The Federal
Aviation Administration (FAA) has approved certain alternative methods
of compliance (AMOC) for AD 97-01-01, and has determined that these
AMOC's should be incorporated into the AD. The proposed AD would retain
all the actions of AD 97-01-01, and would incorporate certain AMOC's as
a way of accomplishing the actions specified in AD 97-01-01. The
actions specified by the proposed AD are intended to prevent a main
landing gear collapse caused by main gear sidebrace stud cracks, which
could result in loss of control of the airplane during landing
operations.
DATES: Comments must be received on or before July 23, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Regional 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: Mr. William O. Herderich, Aerospace
Engineer, FAA, Atlanta Certification Office, One Crown Center, 1895
Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone: (770)
703-6084; facsimile: (770) 703-6097.
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
[[Page 28295]]
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 Regional Counsel, Attention:
Rules Docket No. 96-CE-09-AD, Room 1558, 601 E. 12th Street, Kansas
City, Missouri 64106.
Discussion
AD 97-01-01, Amendment 39-9872 (62 FR 10, January 2, 1997),
currently requires repetitively inspecting the main gear sidebrace
studs for cracks on Piper Models PA-24, PA-28R, PA-30, PA-32R, PA-34,
and PA-39 series airplanes, and replacing any main gear sidebrace stud
found cracked. The actions specified by AD 97-01-01 are intended to
prevent a main landing gear collapse caused by main gear sidebrace stud
cracks, which could result in loss of control of the airplane during
landing operations.
Actions Since Issuance of Previous Rule
Since issuance of AD 97-01-01, the FAA has approved alternative
methods of compliance for modifying the existing bracket assembly as
terminating action for the repetitive inspection requirement of that
AD.
The FAA's Determination
After examining the circumstances and reviewing all available
information related to the subject described above, the FAA has
determined that (1) the alternative methods of compliance approved for
modifying the existing bracket assembly should be made available as an
option of complying with the current AD; and (2) AD action should be
taken to prevent a main landing gear collapse caused by main gear
sidebrace stud cracks, which could result in loss of control of the
airplane during landing operations.
Explanation of the Provisions of the Proposed AD
Since an unsafe condition has been identified that is likely to
exist or develop in other Piper Models PA-24, PA-28R, PA-30, PA-32R,
PA-34, and PA-39 series airplanes of the same type design, the FAA is
proposing to revise AD 97-01-01. The proposed AD would retain all the
actions of AD 97-01-01, and would incorporate alternative methods of
compliance for modifying the existing bracket assembly, as terminating
action for the repetitive inspection requirement of that AD.
Cost Impact
The cost impact of the proposed AD would be the same as is
currently required by AD 97-01-01. As a courtesy, the FAA is reprinting
that cost information in the following paragraphs.
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 (which was superseded by AD 97-01-01). The only
difference between the proposed AD and AD 95-20-07 is the addition of
an inspection-terminating modification option and the elimination of
(from the ``Applicability'' section of the AD) certain airplanes that
incorporate a certain main side brace stud assembly. The proposed AD
would also not provide any additional cost impacts over that already
required by AD 95-20-07.
Regulatory Impact
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
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.
Sec. 39.13 [Amended]
2. Section 39.13, is amended by removing Airworthiness Directive
97-01-01, Amendment 39-9872 (62 FR 10, January 2, 1997), and by adding
a new AD to read as follows:
The New Piper Aircraft, Inc.: Docket No. 96-CE-09-AD; Revises AD 97-
01-01, Amendment 39-9872.
Applicability: The following airplane models and serial numbers,
certificated in any category:
1. All serial numbers of Models PA-24, PA-24-250, PA-24-260, PA-
24-400, PA-30, and PA-39 airplanes;
2. The following model and serial number airplanes that are not
equipped with a Piper part number (P/N) 78717-02 (or FAA-approved
equivalent part number) main gear sidebrace stud in both right and
left main gear sidebrace bracket assemblies:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
PA-28R-180............................ 28R-30002 through 28R-31135, and
28R-7130001 through 28R-
7130013.
PA-28R-200............................ 28R-35001 through 28R-35820, and
28R-7135001 through 28R-
7635539.
PA-28R-201............................ 28R-7737002 through 28R-7737096.
PA-28R-201T........................... 28R-7703001 through 28R-7703239.
PA-32R-300............................ 32R-7680001 through 32R-7780444.
[[Page 28296]]
PA-34-200............................. All serial numbers.
PA-34-200T............................ 34-7570001 through 34-7770372.
------------------------------------------------------------------------
Note 1: P/N 78717-02 sidebrace stud was installed at manufacture
on Piper Model PA-34-200T 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 PA-28R-180, PA-28R-200, PA-28R-201,
PA-28R-201T, PA-32R-300, PA-34-200, and PA-34-200T airplanes: Within
the next 100 hours time-in-service (TIS) after the effective date of
this AD; or, if the main gear sidebrace 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 PA-24, PA-24-250, PA-24-260, PA-24-
400, PA-30, and PA-39 airplanes: Within the next 100 hours TIS after
the effective date of this AD; or, if the main gear sidebrace 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
sidebrace stud cracks, which 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 4: (A), (B), (C), etc.
Level 2, Level 3, and Level 4 structures are designations of the
Level 1 paragraph they immediately follow.
(a) Remove both the left and right main gear sidebrace studs
from the airplane in accordance with the instructions contained in
the Landing Gear section of the maintenance manual, and inspect each
main gear sidebrace stud for cracks, using Type I (fluorescent)
liquid penetrant or magnetic particle inspection methods. Figure 1
of this AD depicts the area of the sidebrace stud shank where the
sidebrace stud is to be inspected.
Note 4: All affected Models PA-24 and PA-24-250 airplanes were
equipped at manufacture with P/N 20829-00 main gear sidebrace studs.
All affected Models PA-24-260, PA-24-400, PA-30, and PA-39 airplanes
were equipped at manufacture with P/N 22512-00 main gear sidebrace
studs. The Appendix included with this AD contains information on
determining the P/N of the bracket assembly (which contains the main
gear side brace stud) on the affected PA-28R, PA-32R, and PA-34
series airplanes.
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[GRAPHIC] [TIFF OMITTED] TP22MY98.001
BILLING CODE 4910-13-C
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(1) For any main gear sidebrace 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 part number) 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 PA-28R-180, PA-28R-200, PA-28R-201,
PA-28R-201T, PA-32R-300, PA-34-200, and PA-34-200T airplanes, the 9/
16-inch main gear sidebrace studs (P/N 95299-00, 95299-02, or P/N
67543, as applicable) are no longer manufactured. Install a new main
gear sidebrace 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 PA-28R-180, PA-28R-200, PA-28R-
201, PA-28R-201T, PA-32R-300, PA-34-200, and PA-34-200T airplanes,
ream the existing two-piece bushings to an inside diameter of .624-
inch to .625-inch, chamfer the head side of the bushing to
accommodate the radius in the shank of the main gear sidebrace stud,
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 bushings are loose), then install a main gear
sidebrace bracket assembly, P/N 95643-06, P/N 95643-07, P/N 95643-
08, or P/N 95643-09, as applicable. Models PA-28R-180 and PA-28R-200
with serial numbers as specified in the Appendix to this AD may be
equipped with a bracket casting identified with casting number
67073-2 or 67073-3 and may require the following modification to P/N
78717-02 for proper installation:
(A) Reduce the length of the stud to 1.688 0.15
inches;
(B) Add additional rolled threads to 1.125 .015
inches from the flange. Note that the stud is heat treated to 180 to
200 ksi; and
(C) Drill an additional roll pin hole 90 degrees to the existing
hole, and approximately 1.480 inches from the flange.
(iv) No repetitive inspections will be required by this AD when
a P/N 78717-02 (or FAA-approved equivalent part number) main gear
sidebrace stud is installed in the existing bracket assembly or when
a bracket assembly, P/N 95643-07 (or FAA-approved equivalent part
number), P/N 95643-08 (or FAA-approved equivalent part number), or
P/N95643-09 (or FAA-approved equivalent part number), as applicable,
is installed.
(2) For any main gear sidebrace 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 sidebrace 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 Model airplanes
Part number installed interval installed on
(hours)
------------------------------------------------------------------------
20829-00 (Piper parts) or FAA- 1,000 PA-24 and PA-24-250.
approved equivalent part number.
22512-00 (Piper parts) or FAA- 1,000 PA-24-260, PA-24-400, PA-
approved equivalent part number. 30, and PA-39.
95299-00 or 95299-02 (Piper 500 PA-28R-180 and PA-28R-
parts) or FAA-approved 200 not equipped with
equivalent part number. casting number 67073-2
or 67073-3, PA-28R-201,
PA-28R-201T, PA-32R-
300, PA-34-200, and PA-
34-200T.
67543 (Piper parts) or FAA- 500 PA-28R-180 and PA-28R-
approved equivalent part number. 200 equipped with
casting number 67073-02
or 67073-03.
------------------------------------------------------------------------
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 PA-24, PA-
30, and PA-39 series airplanes.
(c) Owners/operators of the affected Models PA-28R-180, PA-28R-
200, PA-28R-201, PA-28R-201T, PA-32R-300, PA-34-200, and PA-34-200T
airplanes may accomplish one of the following at any time to
terminate the repetitive inspection requirement of this AD:
(1) Install a main gear sidebrace bracket assembly, P/N 95643-06
(or FAA-approved equivalent part number), P/N 95643-07 (or FAA-
approved equivalent part number), P/N 95643-08 (or FAA-approved
equivalent part number), or P/N 95643-09 (or FAA-approved equivalent
part number), as applicable, which contains the 5/8-inch diameter
main gear sidebrace stud, P/N 78717-02 (or FAA-approved equivalent
part number), and the one-piece bushing, P/N 67026-12 (or FAA-
approved equivalent part number). Accomplish these installations in
accordance with the instructions contained in the Landing Gear
section of the applicable maintenance manual; or
(2) Ream the existing two-piece bushings to an inside diameter
of .624-inch to .625-inch, chamfer the head side of the bushing to
accommodate the radius in the shank of the main gear sidebrace stud,
and install the 5/8-inch stud, P/N 78717-02 (or FAA-approved
equivalent part number). 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 bushings are
loose), then install a main gear sidebrace bracket assembly, P/N
95643-06 (or FAA-approved equivalent part number), P/N 95643-07 (or
FAA-approved equivalent part number), P/N 95643-08 (or FAA-approved
equivalent part number), or P/N 95643-09 (or FAA-approved equivalent
part number), as applicable. Models PA-28R-180 and PA-28R-200 with
serial numbers as specified in the Appendix to this AD may be
equipped with a bracket casting identified with casting number
67073-2 or 67073-3 and may require the following modification to P/N
78717-02 (or FAA-approved equivalent part number) for proper
installation:
(i) Reduce the length of the stud to 1.688 0.15
inches;
(ii) Add additional rolled threads to 1.125 .015
inches from the flange. Note that the stud is heat treated to 180 to
200 ksi; and
(iii) Drill an additional roll pin hole 90 degrees to the
existing hole, and approximately 1.480 inches from the flange.
(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), One Crown Center, 1895 Phoenix
Boulevard, suite 450, Atlanta, Georgia 30349.
(1) The request shall be forwarded through an appropriate FAA
Maintenance Inspector, who may add comments and then send it to the
Manager, Atlanta ACO.
(2) Alternative methods of compliance approved in accordance
with AD 97-01-01, Amendment 39-9872 (revised by this action), or AD
95-20-07, Amendment 39-9386 (superseded by AD 97-01-01), are
considered approved as alternative methods of compliance with this
AD.
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) Information related to this AD may be inspected at the FAA,
Central Region, Office of the Regional Counsel, Room 1558, 601 E.
12th Street, Kansas City, Missouri.
[[Page 28299]]
(g) This amendment revises AD 97-01-01, Amendment 39-9872, which
superseded AD 95-20-07, Amendment 39-9386.
Appendix to Docket No. 96-CE-09-AD Information to Determine Main Gear
Sidebrace Stud Assembly Part Number (P/N)
--The P/N 95643-00/-01/-02/-03 bracket assembly contains the 9/16-
inch diameter main gear sidebrace 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 sidebrace 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. This measurement is not valid for the following
airplanes:
------------------------------------------------------------------------
Model Serial Nos.
------------------------------------------------------------------------
PA-28R-180............................ 28R-30004 through 28-31270.
PA-28R-200............................ 28R-35001 through 28R-35820, and
28R-7135001 through 28R-
7135062.
------------------------------------------------------------------------
The main gear sidebrace studs on these airplanes will require
removal to determine the P/N installed.
--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 sidebrace stud
will need to be removed from the bracket to determine the shank
diameter and main gear sidebrace stud P/N.
--P/N 95299-00 and P/N 95299-02 main gear sidebrace studs are 9/16-
inch in diameter.
--P/N 78717-00 main gear sidebrace studs are 5/8-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 sidebrace stud, P/N
78717-02.
--The embossed number of 95363 on the bracket forging is not the
bracket assembly P/N.
--The bracket assemblies identified with casting number 67073-2 or
67073-3 contain a 9/16-inch diameter main gear sidebrace stud, P/N
67543, and two-piece bushing, P/N 67026-2 and 67026-3.
--Model PA-28R-180 airplanes, serial numbers 28R-30004 through 28R-
31270; and Model PA-28R-200 airplanes, serial numbers 28R-35001
through 28R-35820 and 28R-7135001 through 28R-7135062, are equipped
from the factory with bracket assemblies identified with casting
number 67073-2 and 67073-3.
--P/N 67543 main gear sidebrace studs are 9/16-inch in diameter.
Issued in Kansas City, Missouri, on May 14, 1998.
Michael Gallagher,
Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-13656 Filed 5-21-98; 8:45 am]
BILLING CODE 4910-13-U