[Federal Register Volume 62, Number 1 (Thursday, January 2, 1997)]
[Rules and Regulations]
[Pages 10-15]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-33231]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-CE-09-AD; Amendment 39-9872; AD 97-01-01]
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: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
supersedes AD 95-20-07, which currently requires repetitively
inspecting the main gear sidebrace 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 sidebrace stud.
This AD retains the repetitive inspection and possible replacement
requirements of AD 95-20-07; specifies in the ``Applicability'' section
of the AD that certain Model PA34-200T airplanes could contain a
certain main gear sidebrace assembly configuration that is not
affected; and incorporates additional modification and replacement
options. This AD results from additional information received by the
Federal Aviation Administration (FAA) after the issuance of AD 95-20-07
on the design and service history of the affected airplanes concerning
this subject. 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: February 7, 1997.
ADDRESSES: Information that applies to this AD may be examined at the
FAA, Central Region, Office of the Assistant Chief Counsel, Attention:
Rules Docket 96-CE-09-AD, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106.
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 This Action
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to Piper PA24, PA28R,
PA30, PA32R, PA34, and PA39 series airplanes was published in the
Federal Register on April 25, 1996 (61 FR 18299). The action proposed
to supersede AD 95-20-07 with a new AD that would (1) retain the
requirement of repetitively inspecting the main gear sidebrace
assembly, and replacing any cracked main gear sidebrace stud. This
includes the inspection-terminating replacement contained in AD 95-20-
07; (2) specify in the ``Applicability'' section of the current AD that
certain Piper Model PA34-200T airplanes could incorporate a main gear
sidebrace assembly containing the \5/8\-inch stud, part number (P/N)
78717-02, with a two-piece bushing, P/N 67026-09, and would not be
affected by the proposed AD; and (3) incorporate, as an option, an
inspection-terminating modification for Piper PA28R, PA32R, and PA34
series 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 bushing, and installing the \5/8\-inch
stud, P/N 78717-02.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the two comments received from one commenter.
Comment Issue No. 1: Include a Specific FAA-Approved Parts Manufacture
Approval (PMA) in the AD as Replacement Parts
The commenter, Webco Aircraft (Webco), states that it holds a PMA
for main gear sidebrace studs to equip the Piper Models PA24, PA24-250,
PA24-260, PA24-400, PA30, and PA39 airplanes. Webco requests that the
FAA
[[Page 11]]
reference these main gear sidebrace studs in the AD.
The FAA does not concur. FAA policy is to not reference PMA parts
in AD's, unless the FAA determines that the unsafe condition applies to
the PMA parts. If these Webco parts are installed, then the actions of
this AD would not apply because the parts are an FAA-approved
equivalent to the Piper main gear sidebrace studs that, when installed,
eliminate the repetitive inspection requirement of the AD.
Comment Issue No. 2: Additional Information Added to the AD
Webco recommends that the FAA add cautionary information to the AD
on reaming and chamfering the existing two-piece bushings, P/N 67026-6,
on the Piper PA-28R, PA-32R, and PA-34 series airplanes. Webco states
that the manufacturing and service limits for the P/N 67026-6 bushings
are so close that reaming could induce gouges that are deeper than the
minimum dimension specified by The New Piper Aircraft, Inc. Webco also
recommends that the FAA incorporate specific guidance into the AD,
emphasizing that only the head side of the bushing requires chamfering
to accommodate the radius in the shank of the sidebrace stud.
The FAA concurs that additional guidance on chamfering the bushing
would be helpful and has reworded the AD to incorporate the commenter's
specific recommendation.
The FAA does not concur that more guidance is needed on reaming the
bushings. The proposal specifies reaming the inside diameter of the
bushings to a dimension of .624-inch to .625-inch. If the bushing is
reamed to a dimension other than that specified in the AD, then
compliance with the AD would not be accomplished.
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
the incorporation of guidance on chamfering the bushings and minor
editorial corrections. The FAA has determined that the incorporation
and 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 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 required action, and that the average labor
rate is approximately $60 an hour. Based on these figures, the total
cost impact of the required inspection on U.S. operators is estimated
to be $3,960,000. This figure represents the total cost of the required
initial inspection, and does not reflect costs for any of the required
repetitive inspections or possible replacements. The FAA has no way of
determining how many main gear sidebrace studs may need replacement or
how many repetitive inspections each owner/operator may incur over the
life of the airplane.
In addition, this AD requires the same inspections required by AD
95-20-07. The only difference between this AD and AD 95-20-07 is the
addition of an inspection-terminating modification option. This AD does
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 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:
97-01-01 The New Piper Aircraft, Inc.: Amendment 39-9782; 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 Piper part number (P/N) 78717-02 main landing gear
sidebrace stud in both right and left main landing gear sidebrace
bracket assemblies:
------------------------------------------------------------------------
Model Serial Nos.
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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.
------------------------------------------------------------------------
Note 1: P/N 78717-02 sidebrace 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
[[Page 12]]
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 PA24, PA24-250, PA24-260, PA24-400,
PA30, and PA39 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 2 and Level 3 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 PA24 and PA24-250 airplanes were
equipped at manufacture with P/N 20829-00 main gear sidebrace studs.
All affected Models PA24-260, PA24-400, PA30, and PA39 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 PA28R, PA32R, and PA34 series
airplanes.
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[GRAPHIC] [TIFF OMITTED] TR02JA97.001
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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) 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 sidebrace studs 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 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, 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. No repetitive inspections will
be required by this AD when this bracket assembly 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 installed
Part No. installed interval on
(hours)
------------------------------------------------------------------------
20829-00 (Piper parts) or FAA- 1,000 PA24 and PA24-250.
approved equivalent.
22512-00 (Piper parts) or FAA- 1,000 PA24-260, PA24-400, PA30,
approved equivalent. and PA39.
95299-00 or 95299-02 (Piper 500 PA28R-180, PA28R-200,
parts) or FAA-approved PA28R-201, PA28R-201T,
equivalent. 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 sidebrace 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 sidebrace 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, 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. 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.
(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.
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.
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 Assistant Chief Counsel, Room 1558,
601 E. 12th Street, Kansas City, Missouri.
(g) This amendment supersedes AD 95-20-07, Amendment 39-9386.
(h) This amendment (39-9782) becomes effective on February 7,
1997.
Appendix to AD 97-01-01 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.
------------------------------------------------------------------------
PA28R-180........................... 28R-30004 through 28-31270.
PA28R-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.
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Issued in Kansas City, Missouri, on December 23, 1996.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 96-33231 Filed 12-31-96; 8:45 am]
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