[Federal Register Volume 63, Number 209 (Thursday, October 29, 1998)]
[Rules and Regulations]
[Pages 57895-57899]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-29003]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-09-AD; Amendment 39-10864; AD 97-01-01 R1]
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: Final rule.
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SUMMARY: This amendment revises AirworthinessDirective (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. This
AD will retain all the actions of AD 97-01-01, and will incorporate
certain AMOC's as a way of accomplishing the actions specified in AD
97-01-01. The actions specified by this 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.
EFFECTIVE DATE: December 8, 1998.
ADDRESSES: This information may also be examined at the Federal
Aviation Administration (FAA), Central Region,Office of the Regional
Counsel, Attention: RulesDocket No. 96-CE-09-AD, Room 1558, 601 E. 12th
Street,Kansas City, Missouri 64106.
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:
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 Piper Models PA-24,
PA-28R, PA-30, PA-32R, PA-34, and PA-39 series airplanes was published
in the Federal Register as a notice of proposed rulemaking (NPRM) on
May 22, 1998 (63 FR 28294). The NPRM proposed to supersede AD 97-01-01,
Amendment 39-9872 (62 FR 10, January 2, 1997), which currently requires
repetitively inspecting the main gear sidebrace studs for cracks on the
above-referenced airplanes, and replacing any main gear sidebrace stud
found cracked. The NPRM proposed to retain all the actions of AD 97-01-
01, and incorporate certain alternative methods of compliance (AMOC's)
as a way of accomplishing the actions specified in AD 97-01-01.
The NPRM was the result of the FAA approving AMOC's for modifying
the existing bracket assembly as terminating action for the repetitive
inspection requirement of that AD.
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'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
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 cost impact of this AD will 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 will
be affected by this AD, that it will take approximately 5 workhours per
airplane to accomplish the initial inspection, and that the average
labor rate is approximately $60 an hour. Based on
[[Page 57896]]
these figures, the total cost impact of the inspection on U.S.
operators is estimated to be $3,960,000. This figure represents the
total cost of the initial inspection, and does not reflect costs for
any of the repetitive inspections or possible replacements. TheFAA 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, this AD will require the same inspections required by
AD 95-20-07 (which was superseded by AD 97-01-01). The only difference
between this 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. This AD will also not provide
any additional cost impacts over that already required by AD 95-20-07.
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, 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13, is amended by removing Airworthiness Directive
(AD) 97-01-01, Amendment 39-9872 (62 FR 10, January 2, 1997), and by
adding a new AD to read as follows:
97-01-01 R1 The New Piper Aircraft, Inc.: Amendment 39-10864;
Docket No. 96-CE-09-AD.
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 numbers
------------------------------------------------------------------------
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.
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] TR29OC98.094
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 on both the left and
right sides; 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 on both the left and right bracket assemblies. 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 on both
the left and right sides; or when a 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/N95643-09 (or FAA-approved equivalent
part number), as applicable, is installed on both the left and right
sides.
(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
Part number installed Interval Model airplanes
(hours) Installed on
------------------------------------------------------------------------
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,
approved equivalent part PA-30, and PA-39.
number.
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 200 equipped with
number. 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 on both the left and
right bracket assemblies. 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.
[[Page 57899]]
(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.
(g) This amendment revises AD 97-01-01, Amendment 39-9872, which
superseded AD 95-20-07, Amendment 39-9386.
(h) This amendment becomes effective on December 8, 1998.
Appendix to AD 97-01-01 R1; Amendment No. 39-10864; 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 numbers
------------------------------------------------------------------------
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 October 22, 1998.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 98-29003 Filed 10-28-98; 8:45 am]
BILLING CODE 4910-13-P