[Federal Register Volume 59, Number 105 (Thursday, June 2, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-13236]


[[Page Unknown]]

[Federal Register: June 2, 1994]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 93-NM-167-AD; Amendment 39-8923; AD 94-11-07]

 

Airworthiness Directives; British Aerospace Model BAC 1-11-200 
and -400 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 all British Aerospace Model BAC 1-11-200 and -400 series 
airplanes, that requires inspection of the landing gear brakes for 
wear, and replacement of the brakes if the wear limits prescribed in 
this amendment are not met. This amendment also requires that the 
specified maximum brake wear limits 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: July 5, 1994.

ADDRESSES: Information pertaining to this rulemaking action may be 
examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Mark 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 BAC 1-11-200 and -400 series 
airplanes was published in the Federal Register on January 27, 1994 (59 
FR 3798). That action proposed to require the inspection of certain 
landing gear brakes for wear, and the replacement of brakes if the wear 
limits prescribed in the proposal are not met. That action also 
proposed that the specified maximum brake wear limits be incorporated 
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 comments received.
    One commenter supports the proposal.
    Another commenter requests that NOTE 2 of the proposal be 
clarified. This commenter points out that proposed NOTE 2 states, ``* * 
* Brake units having wear indicators set at 1.06 inch will be 
considered to be fully worn when either wear indicator pin is 1.0 inch 
or less above the surface of the carrier. * * *'' In effect, this 
wording permits a total brake wear (from new to fully worn brake) of 
only 0.06 inch. This clearly is incorrect. This commenter states that a 
correctly set wear indicator pin protrudes above the surface of the 
carrier when in normal operation, but will be flush with the surface 
when the brake is fully worn. Thus, the dimension by which the pin 
protrudes above the surface of the carrier is the amount of wear still 
available. Therefore, a wear indicator pin set for the existing limit 
of 1.06 inch will protrude above the surface of the carrier by 0.06 
inch when the new wear limit of 1.00 inch is reached. The FAA concurs 
and has revised NOTE 2 of the final rule to clarify this point.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 100 Model BAC 1-11-200 and -400 series 
airplanes of the affected design in the worldwide fleet.
    The FAA estimates that 10 Model BAC 1-11-200 series airplanes of 
U.S. registry and 2 U.S. operators of these airplanes will be affected 
by this proposed AD. For these airplanes and operators, although the 
rule requires the incorporation of maximum brake wear limits into the 
FAA-approved maintenance inspection program, no other specific 
additional action, inspection, or part replacement costs relative to 
that requirement is involved; such actions are currently a part of the 
current maintenance program. However, it is estimated that it will take 
approximately 1 work hour, at an average labor rate of $55 per work 
hour, for each operator to incorporate the revision into its FAA-
approved maintenance inspection program. Based on these figures, the 
total cost impact of the requirement to revise the FAA-approved 
maintenance inspection program on U.S. operators of Model BAC 1-11-200 
series airplanes is estimated to be $110, or $55 per operator.
    The FAA estimates that 20 Model BAC 1-11-400 series airplanes of 
U.S. registry and 19 U.S. operators of these airplanes will be affected 
by this AD. It is estimated that it will take approximately 1 work 
hour, at an average labor rate of $55 per work hour, for each operator 
to incorporate the revision into its FAA-approved maintenance 
inspection program. Based on these figures, the total cost impact of 
that requirement on U.S. operators of Model BAC 1-11-400 series 
airplanes is estimated to be $1,045, or $55 per operator.
    Additionally, the FAA estimates that for operators of Model BAC 1-
11-400 series airplanes, it will take approximately 2 work hours per 
airplane to shorten the wear pins for replacement brakes, and 8 work 
hours per airplane to change the brakes, at an average labor rate of 
$55 per work hour. The cost of required parts to accomplish the change 
in wear limits for these airplanes (that is, the cost resulting from 
the requirement to change the brakes before they are worn to their 
previously approved limits for a one-time change) is estimated to be 
$912 per airplane. Based on these figures, the total cost impact of 
these requirements on U.S. operators of Model BAC 1-11-400 series 
airplanes is estimated to be $29,240, or $1,462 per airplane.
    The total cost impact figures discussed above are 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:

94-11-07 British Aerospace: Amendment 39-8923. Docket 93-NM-167-AD.

    Applicability: All Model BAC 1-11-200 and -400 series airplanes, 
certificated in any category.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent the loss of brake effectiveness during a high energy 
rejected takeoff (RTO), accomplish the following:
    (a) Within 180 days after the effective date of this AD, 
accomplish paragraphs (a)(1) and (a)(2) of this AD.
    (1) Inspect main landing gear brakes having the brake part 
numbers listed below for wear. Any brake worn more than the maximum 
wear limit specified below must be replaced, prior to further 
flight, with a brake within that limit. 

 British Aerospace Model BAC 1-11-200 and -400 Series Airplanes Equipped
                           With Bendix Brakes                           
------------------------------------------------------------------------
                                                    Maximum brake wear  
    Airplane model           Brake part No.           limit (inch/mm)   
------------------------------------------------------------------------
BAC 1-11-200             2601225-1..............  0.75 inch (19.1 mm)   
BAC 1-11-400             2601240-1..............  1.0 inch (25.4 mm)    
------------------------------------------------------------------------

    Note 1: Measuring instructions for Bendix brakes can be found in 
Revision 4 of the Allied Signal Component Maintenance Manual.

    Note 2: Revision 4 of the Allied Signal Component Maintenance 
Manual specifies a brake wear limit of 1.06 inch for brake part 
number 2601240-1. That brake wear limit is superseded by the brake 
wear limit of 1.0 inch specified above for that brake part number. 
Revision 5 of the Allied Signal Component Maintenance Manual will 
reflect the revised brake wear limit of 1.0 inch. Brake units having 
wear indicators set at 1.06 inch will be considered to be fully worn 
when either wear indicator pin is 0.06 inch or less above the 
surface of the carrier, provided the wear indicator pin has not been 
shortened on that brake unit.

    Note 3: Each operator should provide a method of identifying 
modified brakes until Revision 5 of the Allied Signal Component 
Maintenance Manual has been issued. Revision 5 of the manual will 
define a method of brake identification and reflect the brake wear 
limits specified above. A paint scheme similar to that used to 
differentiate between new and refurbished brakes could be used, for 
example, if a different color is used.

    (2) Incorporate into the FAA-approved maintenance inspection 
program the maximum brake wear limits specified in paragraph (a)(1) 
of this AD.
    (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 4: 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 
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.
    (d) This amendment becomes effective on July 5, 1994.

    Issued in Renton, Washington, on May 25, 1994.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 94-13236 Filed 6-1-94; 8:45 am]
BILLING CODE 4910-13-U