[Federal Register Volume 66, Number 228 (Tuesday, November 27, 2001)]
[Proposed Rules]
[Pages 59185-59188]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-29428]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-75-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 757-200, -200CB, and -
200PF; and 767-200, -300, and -300F Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain Boeing Model 757-200, 
200CB, and -200PF; and 767-200, -300, and -300F series airplanes. This 
proposal would require modification of the right main landing gear and 
auto-speedbrake control system to provide an air/ground signal to the 
system. This action is necessary to prevent uncommanded deployment of 
the auto-speedbrake spoilers during flight, which could result in 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by January 11, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-75-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-75-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
Washington 98124-2207. This information may be examined at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington.

FOR FURTHER INFORMATION CONTACT: Barbara Mudrovich, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, FAA, Seattle Aircraft 
Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055-
4056; telephone (425) 227-2983; fax (425) 227-1181.

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 shall 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 action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.

[[Page 59186]]

     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 summarizing 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 action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-75-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, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-75-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received a report of two incidents of in-flight auto-
speedbrake deployment during landing approach on a Boeing Model 767 
series airplane. In one incident, the airplane was at approximately 
1,500 feet altitude with the landing gear down and the auto-speedbrake 
spoilers armed. There was a vibration and the spoilers automatically 
deployed to 20 degrees during flap extension. Investigation revealed 
that an incorrect air/ground data input from the proximity switch 
electronics unit (PSEU) can deploy the auto-speedbrake spoilers. The 
auto-speedbrake system uses only input from the PSEU as its source for 
air/ground data, but this single source of air/ground data may not be 
adequate, in that incorrect data could result in uncommanded deployment 
of the auto-speedbrake spoilers in flight. Uncommanded deployment of 
the auto-speedbrake spoilers during flight, if not corrected, could 
result in reduced controllability of the airplane.
    Boeing Model 757 series airplanes have a similar auto-speedbrake 
control system, therefore, those airplanes may also be subject to the 
same unsafe condition described above.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletins 
757-27A0130, dated August 31, 2000, and 767-27A0160, dated December 20, 
2000, which describe the following modification procedures:

 
------------------------------------------------------------------------
                                     Boeing Alert Service Bulletin 757-
          Work  package                           27A0130
------------------------------------------------------------------------
1................................  Install the truck tilt sensor wire
                                    bundle between the main equipment
                                    compartment and the right main
                                    landing gear (MLG).
2................................  Install a truck tilt sensor and
                                    target on the right MLG. Replace the
                                    terminal rail in the forward
                                    junction box and the electrical
                                    conduits between the box and the
                                    truck tilt sensor. Install sensor
                                    wires to the truck tilt sensor.
3................................  Install a wire between the P36 and
                                    P37 panel assemblies in the main
                                    equipment compartment. The tilt
                                    sensor wires are installed in the
                                    P36 and P37 panel assemblies, and
                                    the tilt sensor relay is installed
                                    in the P37 panel assembly. Do the
                                    system functional tests.
                                   (The service bulletin specifies that
                                    each work package can be done
                                    independently or at the same time,
                                    in any sequence, but the functional
                                    tests in Work Package 3 should be
                                    done last.)
------------------------------------------------------------------------


 
------------------------------------------------------------------------
                                     Boeing Alert Service Bulletin 767-
          Work  package                           27A0160
------------------------------------------------------------------------
1................................  Install the truck tilt sensor wiring
                                    between the main electronic
                                    equipment center disconnect to the
                                    right MLG of the forward cargo
                                    compartment.
2................................  Replace the J2 and J4 junction boxes
                                    and conduit on the right MLG.
                                    Install new truck tilt sensor
                                    wiring.
3................................  Install new truck tilt proximity
                                    sensor and target on the right MLG.
4................................  Install truck tilt sensor wiring to
                                    the P33 forward miscellaneous
                                    electronic equipment panel of the
                                    main electronic equipment center. Do
                                    the wiring changes to the P36 left
                                    miscellaneous electronic equipment
                                    panel. Install a new gear tilt relay
                                    in the P33 panel.
                                   Do a system checkout test to make
                                    sure the truck tilt sensor and auto-
                                    speedbrake, engine probe heat, pitot
                                    probe heat, auto ice detection,
                                    antiskid, tire pressure indication,
                                    brake temperature monitoring, and
                                    brake cooling fan systems operate
                                    properly.
                                   (The service bulletin specifies that
                                    each work package can be done
                                    independently or at the same time,
                                    in any sequence, but Work Package 4
                                    should be done last.)
------------------------------------------------------------------------

    Accomplishment of the actions specified in the service bulletins is 
intended to adequately address the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletins described previously, except as discussed below.

Related Rulemaking

    Boeing Alert Service Bulletin 767-27A0160, is cited in this 
proposed AD as the correct source of service information for doing 
certain actions. That service bulletin references five other related 
service bulletins that should be done before, or concurrently, with 
this proposed AD. Those service bulletins have been addressed in the 
previously issued ADs listed below:
     On July 28, 1994, the FAA issued AD 94-16-03, amendment 
39-8993 (59 FR 41229, August 11, 1994), applicable to certain Boeing 
Model 767 series airplanes equipped with Pratt & Whitney JT9D-7R4 or 
General Electric CF6-80A series engines, which requires inspections, 
adjustments, and functional tests of the thrust reverser system. That 
AD also requires installation of an additional thrust reverser system 
locking feature, periodic functional tests of that locking feature 
following its

[[Page 59187]]

installation, and repair of any discrepancy found. (The service 
bulletins cited in that AD are Boeing Service Bulletins 767-78-0061, 
Revision 1, and 767-78-0060, Revision 2, both dated August 5, 1993.)
     On February 27, 1996, the FAA issued AD 95-13-12 R1, 
amendment 39-9528 (61 FR 9092, March 7, 1996), applicable to certain 
Boeing Model 767 series airplanes equipped with General Electric CF6-
80C2 series engines, which requires tests, inspections, and adjustments 
of the thrust reverser system. That AD also requires installation of a 
terminating modification and repetitive follow-on actions. (The service 
bulletin cited in that AD is Boeing Service Bulletin 767-78-0063, 
Revision 1, dated April 29, 1993.
     On June 3, 1994, the FAA issued AD 94-12-10, amendment 39-
8938 (59 FR 31508, June 20, 1994), applicable to certain Boeing Model 
767 series airplanes equipped with Pratt & Whitney PW4000 series 
engines, which requires repetitive inspections, tests, adjustments, and 
functional checks of the thrust reverser system and of selected engine 
wiring. That AD also requires installation of a terminating 
modification, repetitive operational checks of that installation, and 
repair of any discrepancy found. (The service bulletin cited in that AD 
is Boeing Service Bulletin 767-78-0062, Revision 1, dated December 17, 
1992.)
     On August 4, 1994, the FAA issued AD 94-17-03, amendment 
39-8998 (59 FR 41647, August 16, 1994), applicable to certain Boeing 
Model 767 series airplanes equipped with Rolls-Royce RB211-524 series 
engines, which requires inspections, adjustments, and functional checks 
of the thrust reverser system, installation of a terminating 
modification, and repetitive operational checks of the gearbox locks 
and the air motor brake following accomplishment of the modification. 
(The service bulletin cited in that AD is Boeing Service Bulletin 767-
78-0059, Revision 1, dated September 24, 1992.)

Difference Between the Proposed AD and Alert Service Bulletins

    The alert service bulletins recommend incorporation of the 
specified actions ``at the earliest maintenance opportunity when 
manpower, materials, and facilities are available,'' the FAA finds that 
such a compliance time will not ensure that the modification is 
accomplished in a timely manner. In developing an appropriate 
compliance time for this AD, the FAA considered not only the 
manufacturer's recommendation, but the degree of urgency associated 
with addressing the subject unsafe condition, the average utilization 
of the affected fleet, and the time necessary to perform the 
modifications. In light of all of these factors, the FAA finds a 36-
month compliance time for accomplishing the modifications on all 
affected airplanes to be warranted, in that it represents an 
appropriate interval of time allowable for affected airplanes to 
continue to operate without compromising safety.

Cost Impact

    There are approximately 1,654 airplanes of the affected design in 
the worldwide fleet. The FAA estimates that 583 Model 757 series 
airplanes and 292 Model 767 series airplanes of U.S. registry would be 
affected by this proposed AD. The work hours and cost estimates for the 
proposed modifications are listed below:

               *Boeing Alert Service Bulletin 757-27A0130
------------------------------------------------------------------------
                 Work hours @ $60/  Cost per airplane      Fleet cost
  Work package           WH           without parts      without parts
------------------------------------------------------------------------
                  1.............50             $3,000         $1,749,000
                  2.............32              1,920          1,119,360
                  3.............12                720           419,760
------------------------------------------------------------------------
*Parts cost for Model 757 series airplanes is between $8,953 and $10,630
  per airplane.


               *Boeing Alert Service Bulletin 767-27A0160
------------------------------------------------------------------------
                 Work hours @ $60/  Cost per airplane      Fleet cost
  Work package           WH           without parts      without parts
------------------------------------------------------------------------
1..............                 11               $660           $192,720
2..............                 18              1,080            315,360
3..............                  2                120             35,040
4..............                 15                900           262,800
------------------------------------------------------------------------
*Parts cost for Model 767 series airplanes is between $7,132 and $8,224
  per airplane.

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the proposed requirements 
of this AD action, and that no operator would accomplish those actions 
in the future if this proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up, planning time, or time 
necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the 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 is contained in the 
Rules Docket.

[[Page 59188]]

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. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

Boeing: Docket  2001-NM-75-AD.
    Applicability: Model 757-200, -200CB, and -200PF series 
airplanes, line numbers 1 through 895 inclusive; and Model 767-200, 
-300, and -300F series airplanes, line numbers 1 through 759 
inclusive; certificated in any category.

    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 request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To provide a second air/ground signal to the auto-speedbrake 
control system to prevent uncommanded deployment of the auto-
speedbrake spoilers during flight, which could result in reduced 
controllability of the airplane, accomplish the following:

Modifications

    (a) Within 36 months after the effective date of this AD: Modify 
the right main landing gear and auto-speedbrake control system 
according to Work Packages 1 through 3 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0130, dated 
August 31, 2000 (for Model 757 series airplanes), or Work Packages 1 
through 4 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 767-27A0160, dated December 20, 2000 (for Model 767 series 
airplanes), as applicable.

    Note 2: Boeing Alert Service Bulletin 757-27A0130 specifies that 
each work package can be done independently or at the same time, in 
any sequence, but the functional tests in Work Package 3 should be 
done last. Boeing Alert Service Bulletin 767-27A0160 specifies that 
each work package can be done independently or at the same time, in 
any sequence, but Work Package 4 should be done last.

Alternative Methods of Compliance

    (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, Seattle Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Seattle ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Seattle ACO.

Special Flight Permit

    (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.

    Issued in Renton, Washington, on November 20, 2001.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-29428 Filed 11-26-01; 8:45 am]
BILLING CODE 4910-13-P