[Federal Register Volume 60, Number 198 (Friday, October 13, 1995)]
[Proposed Rules]
[Pages 53314-53316]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-25438]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-CE-37-AD]
Airworthiness Directives; The New Piper Aircraft, Inc. (Formerly
Piper Aircraft Corporation) PA28, PA32, PA34, and PA44 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes to adopt a new airworthiness directive
(AD) that would apply to certain New Piper Aircraft, Inc. (Piper) PA28,
PA32, PA34, and PA44 series airplanes. The proposed action would
require inspecting and modifying the flap lever assembly. Reports of
worn flap handle attach bolts and elongated holes in the flap lever to
cable mounting attach point prompted this proposed AD action. The
actions specified by the proposed AD are intended to prevent failure of
the flap handle attach bolt and sudden retraction of the flaps, which,
if not detected and corrected, could result in possible loss of control
of the airplane.
DATES: Comments must be received on or before December 14, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Central Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-CE-37-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.
Piper Service Bulletin (SB) No. 965, dated September 1, 1993, may
be obtained from The New Piper Aircraft, Inc., Attn: Customer Service,
2629 Piper Dr., Vero Beach, Florida 32960. This information also 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. 95-CE-37-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. 95-CE-37-AD, Room 1558, 601 E. 12th Street,
Kansas City, Missouri 64106.
Discussion
The FAA has received reports of worn flap handle attach bolts and
elongated holes in the flap lever to cable mounting attach points on
certain Piper PA28, PA32, PA34, and PA44 series airplanes. This
condition, if left uncorrected, could result in the inability to lower
the flaps or, if the retaining bolt breaks or comes free while the
flaps are in a down position, a sudden retraction of the flaps creating
a reduction in lift and possible loss of control of the airplane.
Piper has issued SB No. 965, dated September 1, 1993, which
specifies procedures for: (1) Measuring and enlarging the cable
mounting attach hole diameter, (2) installing a new bushing (Piper Part
Number (P/N) 63900-174), (3) replacing the flap lever handle attach
bolt with a new clevis bolt (Piper P/N 400 673), and (4) inspecting the
washer (P/N 407-584), nut (P/N 404-392), and cotter pin (P/N 424-051)
for damage, and replacing as applicable.
After examining the circumstances and reviewing all available
information related to the incidents described above, the FAA has
determined that AD action should be taken to prevent failure of the
flap handle attach bolt and sudden
[[Page 53315]]
retraction of the flaps, which, if not detected and corrected, could
result in loss of control of the airplane.
Since an unsafe condition has been identified that is likely to
exist or develop in other Piper PA28, PA32, PA34, and PA44 series
airplanes of the same type design, the proposed AD would require (1)
measuring and enlarging the cable mounting attach point hole diameter
to .316 of an inch and if the measurement is larger than .316 of an
inch, replacing the flap lever; (2) installing a new bushing (Piper P/N
63900-174) for increased durability of the joint; (3) replacing the
flap lever handle attach bolt with a new clevis bolt (Piper P/N 400
673), and (4) inspecting the washer (P/N 407-584), nut (P/N 404-392),
and cotter pin (P/N 424-051) for damage, and replacing as applicable.
The FAA estimates that 30,000 airplanes in the U.S. registry would
be affected by the proposed AD, that it would take approximately 2
workhours per airplane to accomplish the proposed action, and that the
average labor rate is approximately $60 an hour. Parts cost
approximately $16 per airplane. Based on these figures, the total cost
impact of the proposed AD on U.S. operators is estimated to be
$4,080,000. This figure is based on the assumption that all of the
affected airplanes have worn bolts and elongated holes and that none of
the owners/operators of the affected airplanes have replaced the worn
parts.
Piper has informed the FAA that parts have been distributed to
equip approximately 8,000 airplanes. Assuming that these distributed
parts are incorporated on the affected airplanes, the cost of the
proposed AD would be reduced by $1,088,000 from $4,080,000 to
$2,992,000.
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding a new airworthiness directive
(AD) to read as follows:
The New Piper Aircraft, Inc. (formerly Piper Aircraft Corporation);
Docket No. 95-CE-37-AD.
Applicability: The following airplane models and serial numbers,
certificated in any category:
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Models Serial No.
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PA-28-140........................... 28-20000 through 28-26946 and 28-
7125001 through 28-7725290.
PA-28-150, PA-28-160, and PA-28-180. 28-1 through 28-5859, 28-7105001
through 28-7505259, 28-E13, and
28-03.
PA-28-151........................... 28-7415001 through 28-7715314.
PA-28-161........................... 28-7716001 through 28-8616057 and
2816001 through 2816102.
PA-28-161........................... 2841001 through 2841346.
PA-28-181........................... 28-7690001 through 28-8690062 and
2890001 through 2890169.
PA-28-235........................... 28-10001 through 28-11378, 28-
7110001 through 28-7710828-77,
and 28-E11.
PA-28-236........................... 28-7911001 through 28-8611008 and
2811001 through 2811034.
PA-28-201T.......................... 28-7921001 through 28-7921095.
PA-28R-180.......................... 28R-30001 through 28R-31270 and
28R-7130001 through 28R-7130013.
PA-28R-200.......................... 28R-35001 through 28R-35820 and
28R-7135001 through 28R-7635462.
PA-28R-201.......................... 28R-7737001 through 28R-7837319
and 2837001 through 2837059.
PA-28R-201T......................... 28R-7703001 through 28R-7803374
and 2803001 through 2803012.
PA-28RT-201......................... 28R-7918001 through 28R-8218026.
PA-28RT-201T........................ 28R-7931001 through 28R-8631005
and 2831001 through 2831038.
PA-32-260........................... 32-1 through 32-1297 and 32-
7100001 through 32-7800008.
PA-32-300........................... 32-40000 through 32-40974 and 32-
7140001 through 32-7940290.
PA-32-301........................... 32-8006001 through 32-8406020.
PA-32-301T.......................... 32-8024001 through 32-8424002.
PA-32R-300.......................... 32R-7680001 through 32R-7880068.
PA-32RT-300......................... 32R-7885001 through 32R-7985105.
PA-32RT-300T........................ 32R-7887001 through 32R-7987126.
PA-32R-301.......................... 32R-8013001 through 32R-8413024.
PA-32R-301T......................... 32R-8029001 through 32R-8429028.
PA-34-200........................... 34-7250001 through 34-7450220.
PA-34-200T.......................... 34-7570001 through 34-8170092.
PA-34-220T.......................... 34-8133001 through 34-8233088.
PA-44-180........................... 44-7995001 through 44-8195026 and
4495001 through 4495013.
PA-44-180T.......................... 44-8107001 through 44-8107066.
------------------------------------------------------------------------
Note 1: 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 use the authority
provided in paragraph (f) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition, or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required upon the accumulation of 2,000 hours time-
in-service (TIS) or within the next 100 hours TIS after the
effective date of this AD, whichever occurs later, unless already
accomplished.
Note 2: The compliance time specified in this AD takes
precedence over the compliance time specified in the Piper Service
Bulletin (SB) 965, dated September 1, 1993.
Note 3: The instructions in the proposed AD do not mirror the
service bulletin and the
[[Page 53316]]
AD instructions take precedence over the service bulletin instructions.
The proposed AD will require installing the clevis bolt, regardless
of the condition of the current part.
To prevent failure of the flap handle attach bolt and sudden
retraction of the flaps, which, if not detected and corrected, could
result in loss of control of the airplane, accomplish the following:
(a) Measure the cable mounting attach hole diameter and enlarge
the hole to .316 of an inch diameter. If the diameter of the cable
mount attach hole is larger than .316 of an inch, prior to further
flight, replace the flap lever handle (refer to the applicable
illustrated parts catalog for part number), in accordance with Piper
SB No. 965, dated September 1, 1993.
(b) Install a new bushing (Piper Part Number (P/N) 63900-174)
into the cable mounting attach hole, in accordance with Piper SB No.
965, dated September 1, 1993.
(c) Replace the flap lever handle attach bolt with a new clevis
bolt (Piper P/N 400 673) in accordance with Piper SB No. 965, dated
September 1, 1993.
(d) Inspect, and if damaged, prior to further flight, replace
the washer (P/N 407-584), nut (P/N 404-392), and cotter pin (P/N
424-051) as applicable in accordance with Piper SB No. 965, dated
September 1, 1993.
(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, FAA, Atlanta Aircraft Certification Office,
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 Aircraft Certification Office.
Note 4: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta Aircraft Certification Office.
(g) All persons affected by this directive may obtain copies of
the document referred to herein upon request to The New Piper
Aircraft, Inc., Attn: Customer Service, 2629 Piper Dr., 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.
Issued in Kansas City, Missouri, on October 6, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-25438 Filed 10-12-95; 8:45 am]
BILLING CODE 4910-13-U
