[Federal Register Volume 60, Number 45 (Wednesday, March 8, 1995)]
[Proposed Rules]
[Pages 12714-12717]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-5601]



========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 60, No. 45 / Wednesday, March 8, 1995 / 
Proposed Rules
[[Page 12714]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-CE-28-AD]


Airworthiness Directives; Piper Aircraft Corporation PA-28 and 
PA-32 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: This document proposes to supersede AD 76-25-06, which 
currently requires replacing certain engine oil hoses on Piper Model 
PA-28-140 airplanes, and inspecting for a minimum clearance between the 
oil hose assemblies and the front exhaust stacks and adjusting if 
proper clearance is not obtained. The proposed action would maintain 
the clearance inspection and hose replacement, require this inspection 
and replacement to be repetitive, and extend the applicability to 
include PA-32 series and other PA-28 series airplanes. It would also 
provide the option of installing an approved TSO-C53a, Type D, hose 
assembly as terminating action for the repetitive inspection 
requirement. Numerous incidents/accidents caused by oil cooler hose 
rupture or failure on the affected airplanes prompted the proposed 
action. The actions specified by the proposed AD are intended to 
prevent these hoses from failing or rupturing, which could result in 
engine stoppage and subsequent loss of control of the airplane.

DATES: Comments must be received on or before May 19, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Central Region, Office of the Assistant Chief 
Counsel, Attention: Rules Docket No. 94-CE-28-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.
    Service information that applies to this AD may be obtained from 
the Piper Aircraft Corporation, Customer Services, 2926 Piper Drive, 
Vero Beach, Florida 32960. This information also may be examined at the 
Rules Docket at the address above.

FOR FURTHER INFORMATION CONTACT: Ms. Juanita Craft-Lloyd, Aerospace 
Engineer, FAA, Atlanta Aircraft Certification Office, Campus Building, 
1701 Columbia Avenue, suite 2-160, College Park, Georgia 30337-2748; 
telephone (404) 305-7373; 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. 94-CE-28-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. 94-CE-28-AD, Room 1558, 601 E. 12th Street, 
Kansas City, Missouri 64106.

Discussion

    AD 76-25-06, Amendment 39-2788, currently requires replacing 
certain engine oil hoses on Piper Model PA-28-140 airplanes, and 
inspecting for a minimum clearance between the oil hose assemblies and 
the front exhaust stacks and adjusting if proper clearance is not 
obtained.
    Since issuance of that AD, the FAA has received over 20 incident 
and accident reports on Piper PA-28 and PA-32 series airplanes where 
the oil cooler hoses either ruptured or failed. Many of these 
occurrences required the pilot to make an emergency landing. In some 
instances, oil spraying from these ruptured hoses contacted the hot 
engine and produced smoke in the cockpit or caused controllability 
problems when sprayed on the windshield.
    Other airplane models have shown a history of oil cooler hose 
problems; however, most of these have been attributed to leaking hoses 
instead of ruptured or broken hoses as detailed in the incident/
accident reports referenced above on the PA-28 and PA-32 series 
airplanes. The close proximity of the oil cooler hoses to the exhaust 
stacks in some of these airplanes also contributes to the hazardous 
nature of these oil cooler hose failures.
    The Model PA-28-140 airplanes in the referenced incidents/accidents 
were in compliance with AD 76-26-05; however, that AD did not establish 
any repetitive oil cooler hose inspection or replacement requirements.
    After examining the circumstances and reviewing all available 
information related to the incidents described above, the FAA has 
determined that (1) the oil cooler assemblies should be repetitively 
inspected for clearance, and the oil cooler hoses should be replaced at 
certain time intervals; (2) the applicability of AD 76-26-05 should be 
extended to include other PA-28 series and the PA-32 series airplanes; 
and (3) AD action should be taken to prevent oil cooler hoses from 
failing or rupturing, which could result in engine stoppage and 
subsequent loss of control of the airplane.
    Since an unsafe condition has been identified that is likely to 
exist or develop in other Piper PA-28 and PA- [[Page 12715]] 32 series 
airplanes of the same type design, the proposed AD would supersede AD 
76-25-06, Amendment 39-2788, with a new AD that would retain the 
clearance inspection and hose replacement for the Piper Model PA-28-140 
airplanes, and make the inspection and replacement repetitive for these 
airplane models as well as other PA-28 series and the PA-32 series 
airplanes. It would also provide the option of installing an approved 
TSO-C53a, Type D, hose assembly as terminating action for the 
repetitive inspection requirement.
    The replacement compliance time for the proposed AD is presented in 
both hours time-in-service (TIS) and calendar time with the prevalent 
compliance time being that which occurs first. Deterioriation or 
failure of the oil cooler hose assemblies could occur as a result of 
normal flight operation or as a result of time. Therefore, the FAA has 
determined that this proposed dual replacement compliance time is 
needed to assure that the oil cooler hose assemblies are replaced 
before they deteriorate and rupture or fail.
    The FAA estimates that 25,000 airplanes in the U.S. registry would 
be affected by the proposed AD, that it would take approximately 2 
workhours (1 workhour inspection and 1 workhour replacement) per 
airplane to accomplish the proposed action, and that the average labor 
rate is approximately $60 an hour. Parts cost approximately $110 per 
airplane. Based on these figures, the total cost impact of the proposed 
AD on U.S. operators is estimated to be $5,750,000. This figure does 
not take into the account the cost of repetitive inspections or 
repetitive replacements. The FAA has no way of determining the number 
of repetitive inspections or replacements each owner/operator would 
incur over the life of the airplane.
    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. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing AD 76-25-06, Amendment 39-
2788, and by adding a new airworthiness directive to read as follows:

Piper Aircraft Corporation: Docket No. 94-CE-28-AD; Supersedes AD 
76-25-06, Amendment 39-2788.

    Applicability: The following airplane models, all serial 
numbers, that are equipped with one of the applicable oil cooler 
hose assembly part numbers (specified below), certificated in any 
category:

------------------------------------------------------------------------
               Models                             Part Nos.             
------------------------------------------------------------------------
PA-28-140..........................  63901-69 or 63901-72.              
PA-28-150, PA-28-160, PA-28S-160,    63635-00, 63636-00, 63701-00, 63901-
 PA-28-180, and PA-28S-180.           20, 63901-26, 63901-43, or 63901- 
                                      72.                               
PA-28R-180, PA-28R-200, and PA-28R-  63901-43.                          
 201.                                                                   
PA-28-151 and PA-28-161............  63901-34 or 63901-49.              
PA-28-181..........................  63901-26, 63901-43, or 63901-50.   
PA-28-235..........................  61413-3, 63901-16, or 63901-26.    
PA-28-236..........................  35801 or 35801-7.                  
PA-32-260..........................  63901-26.                          
PA-32-300, PA-32S-300, and PA-32-    63901-26, 63901-35, or 63901-73.   
 301.                                                                   
PA-32R-300, PA-32RT-300, PA-32R-     63901-98, 63901-99, or 63901-100.  
 301(SP), and PA-32R-301(HP).                                           
PA-32RT-300T, PA-32R-301T, and PA-   63901-26 or 63901-91.              
 32-301T.                                                               
------------------------------------------------------------------------

    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 aircraft from the applicability of this AD.

    Compliance: Required as indicated in the body of this AD, unless 
already accomplished.
    To prevent oil cooler hoses from failing or rupturing, which 
could result in engine stoppage and subsequent loss of control of 
the airplane, accomplish the following:
    (a) Within the next 100 hours time-in-service (TIS) after the 
effective date of this AD, and thereafter at intervals not to exceed 
100 hours TIS, inspect the oil cooler hoses to ensure that the hoses 
meet the criteria presented in the paragraphs below.
    (1) For airplanes that have any oil cooler mounted at the front 
or back of the airplane, or both, the fire sleeve of the hose should 
not be soaked with oil or have a brownish or whitish color, and 
there should be no evidence of deterioration as a result of heat, 
brittleness, or oil seepage. Prior to further flight, replace any 
hose that is soaked with oil, has a brownish or whitish color, or 
has evidence of deterioration.
    (2) On airplanes that have any oil cooler mounted in the front 
of the airplane, ensure that the following exists, and, prior to 
further flight, adjust accordingly:
    (i) The hose passes underneath and behind the electrical ground 
cable and in front of the lower of the two engine mount struts when 
the hose is routed to the rear of the engine; and
    (ii) The hose is tied to the engine mount strut and a clearance 
of at least 2 inches exists between the oil hose and exhaust stack.

    Note 2: Figure 1 of this AD relates to the conditions specified 
in paragraphs (a)(2)(i) and (a)(2)(ii) of this AD.

                                                 BILLING CODE 4910-13-U
[[Page 12716]]

[GRAPHIC][TIFF OMITTED]TP08MR95.001


BILLING CODE 4910-13-C
[[Page 12717]]

    (b) Upon the accumulation of 8 years or 1,000 hours TIS on the 
oil cooler assembly, whichever occurs first, and thereafter at every 
8 years or 1,000 hours TIS (whichever occurs first), accomplish one 
of the following:
    (1) Replace the oil cooler hose assembly with a part number 
specified in the APPLICABILITY section of this AD, and reinspect in 
accordance with paragraph (a) of this AD at intervals not to exceed 
100 hours TIS; or
    (2) Replace the oil cooler assembly with an approved TSO-C53a, 
Type D, hose assembly ensuring that there is a minimum of 2 inches 
between the oil cooler hoses and exhaust stacks (as applicable) upon 
installation.
    (c) The replacement specified in paragraph (b)(2) of this AD may 
be accomplished at any time prior to the 8-year or 1,000-hour 
compliance time as terminating action for the 100-hour TIS 
repetitive inspection requirement of this AD.
    (d) After adjusting or installing oil cooler hoses, prior to 
further flight, run the engine for 5 minutes to ensure that there 
are no oil leaks and that the 2-inch clearance is maintained (as 
applicable) when the engine is warm. Prior to further flight, 
replace any leaking oil cooler hoses and adjust the clearance 
accordingly.

    Note 3: Although not required by this AD, it is recommended that 
a hose flexibility test be accomplished at each 100-hour TIS 
inspection interval. Hose flexibility may be determined by gently 
lifting the hose in several places from the bottom of its downward 
arc to the oil cooler. If the hose moves slightly either from side-
to-side or upward with the hand at the center of an even arc, then 
some flexibility remains. If the hose appears hardened or 
inflexible, hose replacement is recommended.

    (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 
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 4: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (g) Figure 1 of this AD may be obtained from the Atlanta ACO at 
the address specified in paragraph (f) of this AD. This document or 
any other information that relates 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 76-25-06, Amendment 39-2788.

    Issued in Kansas City, Missouri, on March 2, 1995.
Henry A. Armstrong,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-5601 Filed 3-7-95; 8:45 am]
BILLING CODE 4910-13-U