[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