[Federal Register Volume 59, Number 34 (Friday, February 18, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-3582]
[[Page Unknown]]
[Federal Register: February 18, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-11-AD; Amendment 39-8827; AD 94-04-07]
Airworthiness Directives; Beech Model 400A Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to certain Beech Model 400A airplanes. This action
requires rework or replacement of certain hubcaps on the main landing
gear. This AD also requires incorporation of procedures into the FAA-
approved maintenance program for inspections of the transducer drive
clip to ensure that the drive clip gap does not exceed a specified
limit. This amendment is prompted by a report that a Beech Model 400A
airplane lost its anti-skid braking system during landing roll out. The
actions specified in this AD are intended to prevent degradation or
loss of braking performance.
DATES: Effective March 7, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of March 7, 1994.
Comments for inclusion in the Rules Docket must be received on or
before April 19, 1994.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 94-NM-11-AD, 1601 Lind Avenue, SW., Renton,
Washington 98055-4056.
The service information referenced in this AD may be obtained from
Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA,
Small Airplane Directorate, Wichita Aircraft Certification Office, 1801
Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at
the Office of the Federal Register, 800 North Capitol Street, NW.,
suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT:Dale A. Vassalli, Aerospace Engineer,
Systems and Equipment Branch, ACE-130W, FAA, Small Airplane
Directorate, Wichita Aircraft Certification Office, 1801 Airport Road,
room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316)
946-4132; fax (316) 946-4407.
SUPPLEMENTARY INFORMATION: The FAA has received a report that a Beech
Model 400A airplane lost its anti-skid braking system during landing
roll out. In addition, the FAA has received reports that other Model
400A airplanes have also experienced similar problems with the anti-
skid system. Although the exact cause of the brake failure is
undetermined, results of tests and inspections of the brakes and the
anti-skid system on these airplanes have revealed that only marginal
engagement may occur between the main wheel hubcap drive clip and the
anti-skid wheel speed transducer. Lack of adequate engagement between
the drive clip and the transducer could cause the transducer to send
erroneous signals to the anti-skid control box. This condition, if not
corrected, could result in degradation or loss of braking performance.
Model 400A airplanes are equipped with a back-up emergency braking
system. Power brake failure procedures contained in the Emergency
Procedures section of the FAA-approved Airplane Flight Manual (AFM)
specify that the required landing distance will increase by
approximately 50 percent when the brakes have failed and the emergency
brake system is activated. This increase assumes that brake failure is
recognized. In certain brake failure conditions caused by the drive
clip not being fully engaged, the pilot may not immediately recognize
the degradation of braking performance. In this case, the required
landing distance could increase by 70 percent or more.
Federal Aviation Regulation (FAR) 25.735 specifies, in part, that
single failures in brake systems are acceptable, as long as the
airplane can be brought to rest under the landing performance
conditions specified in FAR 25.125 with a mean deceleration during the
landing roll of at least 50 percent of that obtained during normal
landing performance. Since Beech Model 400A airplanes operate under
part 91 of the FAR, the AFM allows landings on a runway as short as the
actual landing distance determined under FAR 25.125, if the normal
brake system is operating. If the normal brake system fails and the
pilot must revert to the emergency brake system, the actual landing
distance required could easily exceed the actual runway length
available.
The FAA has reviewed and approved Beechcraft Service Bulletin No.
2549, dated January 1994, that describes procedures for replacement of
certain hubcaps on the main landing gear with new hubcaps, or rework
and reidentification of certain hubcaps. The rework involves adding a
spacer between the hubcap drive clip and the hubcap, and reidentifying
the hubcap assembly with a specified part number. Accomplishment of
these actions will prevent loss of anti-skid braking action due to
intermittent wheel speed transducer signals. The service bulletin also
describes procedures for an inspection of the transducer drive clip to
ensure that the drive clip gap does not exceed a specified limit. The
Beechcraft service bulletin references Crane Hydro-Aire Service
Bulletin No. 140-031-32-1, dated December 17, 1993, as an additional
source of service information.
Since an unsafe condition has been identified that is likely to
exist or develop on other Model 400A airplanes of the same type design,
this AD is being issued to prevent degradation or loss of braking
performance. This AD requires rework or replacement of certain hubcaps
on the main landing gear. This AD also requires incorporation of
procedures into the FAA-approved maintenance program for inspections of
the transducer drive clip to ensure that the drive clip gap does not
exceed a specified limit. The rework or replacement is required to be
accomplished in accordance with the Beechcraft service bulletin
described previously. The inspection procedure is also referenced in
that service bulletin.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications shall identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption addresses. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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
AD 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 Number 94-NM-11-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, may
be obtained from the Rules Docket at the location provided under the
caption Addresses.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 14 CFR part
39 of the Federal Aviation Regulations 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 adding the following new
airworthiness directive:
94-04-07 Beech Aircraft Corporation: Amendment 39-8827. Docket 94-
NM-11-AD.
Applicability: Model 400A airplanes; serial numbers RK-1 through
RK-23 inclusive, on which BEECHCRAFT Kit No. 128-8001-1 S (increased
landing weight modification) is installed; and serial numbers RK-24
through RK-76 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent degradation or loss of braking performance,
accomplish the following:
(a) Within 25 hours time-in-service or 30 days after the
effective date of this AD, whichever occurs first, accomplish the
requirements of paragraphs (a)(1) and (a)(2) of this AD:
(1) Replace the existing left- and right-hand hubcaps on the
main landing gear with new hubcaps, part number 140-03121-1; or
rework the existing hubcaps by adding a spacer between the hubcap
drive clip and the hubcap and reidentifying the hubcap assembly as
part number 140-03121-1; in accordance with Beechcraft Service
Bulletin No. 2549, dated January 1994.
(2) Incorporate into the FAA-approved maintenance inspection
program the procedure described in Beechcraft Service Bulletin No.
2549, dated January 1994, for inspecting the transducer drive clip
to ensure that the drive clip gap does not exceed 0.20 inch, which
must be accomplished each time a hubcap is removed.
Note 1: The Beechcraft service bulletin references Crane Hydro-
Aire Service Bulletin No. 140-031-32-1, dated December 17, 1993, as
an additional source of service information.
(b) After the effective date of this AD, no person shall install
a hubcap assembly, part number 140-03121, on any airplane.
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, Wichita Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Wichita ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Wichita ACO.
(d) Special flight permits may be issued in accordance with
Federal Aviation Regulations (FAR) 21.197 and 21.199 to operate the
airplane to a location where the requirements of this AD can be
accomplished.
(e) The rework and replacement shall be done in accordance with
Beechcraft Service Bulletin No. 2549, dated January 1994. This
incorporation by reference was approved by the Director of the
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Copies may be obtained from Beech Aircraft Corporation, P.O. Box
85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington; or at the FAA, Wichita Aircraft Certification Office,
1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas;
or at the Office of the Federal Register, 800 North Capitol Street,
NW., suite 700, Washington, DC.
(f) This amendment becomes effective on March 7, 1994.
Issued in Renton, Washington, on February 10, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 94-3582 Filed 2-17-94; 8:45 am]
BILLING CODE 4910-13-U
