[Federal Register Volume 59, Number 76 (Wednesday, April 20, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-9469]


[[Page Unknown]]

[Federal Register: April 20, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-NM-92-AD; Amendment 39-8891; AD 94-09-03]

 

Airworthiness Directives; British Aerospace Model BAe 146 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain British Aerospace Model BAe 146 series airplanes, 
that requires that the brake wear limits prescribed in this proposal be 
incorporated into the FAA-approved maintenance inspection program. This 
amendment is prompted by an accident in which a transport category 
airplane executed a rejected takeoff (RTO) and was unable to stop on 
the runway due to worn brakes; and the subsequent review of allowable 
brake wear limits for all transport category airplanes. The actions 
specified by this AD are intended to prevent the loss of brake 
effectiveness during a high energy RTO.

EFFECTIVE DATE: May 20, 1994.

ADDRESSES: Information concerning this amendment may be obtained from 
or examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Mark I. Quam, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206) 
227-2145; fax (206) 227-1320.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations to include an airworthiness directive (AD) that is 
applicable to all British Aerospace Model BAe 146 series airplanes 
equipped with Dunlop brakes was published in the Federal Register on 
October 21, 1993 (58 FR 54310). That action proposed to require the 
incorporation of the specified maximum wear limits for the specified 
brakes into the FAA-approved maintenance inspection program.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed rule.
    After careful review of the available data, including the comment 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed.
    The FAA estimates that 45 airplanes of U.S. registry and 6 U.S. 
operators that will be affected by this AD. Although this amendment 
will require the incorporation of maximum brake wear limits into the 
FAA-approved maintenance inspection program, no other specific 
additional action, inspection, or part replacement costs are involved; 
such actions are currently a part of the normal maintenance program. 
However it is estimated that it will take approximately 20 work hours, 
at an average labor rate is $55 per work hour, for each operator to 
incorporate the requirement into its FAA-approved maintenance 
inspection program. Based on these figures, the total cost impact of 
the AD on U.S. operators is estimated to be $6,600, or $1,100 per 
operator.
    The total cost impact figure discussed above is based on 
assumptions that no operator has yet accomplished any of the 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.
    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 final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it 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, 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:

94-09-03 British Aerospace: Amendment 39-8891. Docket 93-NM-92-AD.

    Applicability: Model BAe 146 series airplanes equipped with 
Dunlop brakes, certificated in any category. -
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent loss of main landing gear braking effectiveness, 
accomplish the following:
    (a) Within 180 days after the effective date of this AD, 
incorporate the maximum brake wear limits specified in the following 
table into the FAA-approved maintenance inspection program and 
comply with these measurements thereafter. 

                             Dunlop Brakes                              
------------------------------------------------------------------------
                                Maximum brake wear limit (inch)--lineal 
Brake type   Brake part No.-    axial wear as measured by the brake wear
                                              pin (inch)                
------------------------------------------------------------------------
Carbon      AHA 1412/13        2.34'' (1.5'' original wear pin setting +
                                0.84'' spacer).                         
Carbon      AHA 1558/59        2.34'' (1.5'' original wear pin setting +
                                0.84'' spacer).                         
Steel       AHA 1455/56-       0.866''.                                 
------------------------------------------------------------------------

    Note 1: The measuring instructions for carbon and steel brake 
thicknesses and instructions for setting the wear pin length 
specified in the BAe 146 airplane maintenance manual (AMM), section 
32-42-24, or in the Dunlop component maintenance manual (CMM), 
Section 32-42-58, are based currently on the minimum brake 
thicknesses specified in the table.

    (b) 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, Standardization Branch, ANM-113, 
FAA, Transport 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, 
Standardization Branch, ANM-113.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (c) 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.
    (d) This amendment becomes effective on May 20, 1994.

    Issued in Renton, Washington, on April 14, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-9469 Filed 4-19-94; 8:45 am]
BILLING CODE 4910-13-U