[Federal Register Volume 66, Number 223 (Monday, November 19, 2001)]
[Proposed Rules]
[Pages 57904-57905]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-28796]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-268-AD]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 767-200 and -300 Series 
Airplanes Powered by Pratt & Whitney JT9D Series Engines

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 767-200 and -
300 series airplanes powered by Pratt & Whitney JT9D series engines. 
This proposal would require replacement of the existing deactivation 
pin, aft cascade pin bushing, and pin insert on each thrust reverser 
half, with new, improved components. This action is necessary to 
prevent failure of the thrust reverser deactivation pins, which could 
result in deployment of the thrust reverser in flight and consequent 
reduced controllability of the airplane. This action is intended to 
address the identified unsafe condition.

DATES: Comments must be received by January 3, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-268-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-268-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, 
1601 Lind Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: John Vann, Aerospace Engineer, 
Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; telephone (425) 227-1024; 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.
     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-268-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-268-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of partial deployments of improperly 
deactivated thrust reversers during landing on Boeing Model 767 series 
airplanes powered by Pratt & Whitney PW4000 series engines. Subsequent 
investigation revealed that, in each event, the thrust reverser had 
been improperly deactivated. This allowed hydraulic pressure to be 
available to the actuators when the reverse thrust levers were 
activated on landing. The pin insert for the deactivation pin was not 
able to withstand the load of a powered deployment and failed. The 
deactivation pin, as well as the pin insert flange, are subject to an 
adverse tolerance stack-up, that reduces their load carrying 
capability, and the pin and insert flanges may not prevent a 
deactivated thrust reverser sleeve from moving during a powered 
deployment. This condition, if not corrected, could result in 
deployment of the thrust reverser in flight and consequent reduced 
controllability of the airplane.
    The deactivation pins, pin bushings, and insert flanges on Model 
767-200 and -300 series airplanes powered by Pratt & Whitney JT9D 
series engines are the same as those on the affected airplanes. 
Therefore, those airplanes may be subject to the same unsafe condition.

Other Relevant Rulemaking

    On December 7, 1999, we issued AD 99-26-02, amendment 39-11462 (64 
FR 71007, December 20, 1999). That AD applies to certain Boeing Model 
747-400 and 767 series airplanes powered by Pratt & Whitney PW4000 
series engines. That AD requires replacement of the existing 
deactivation pin, pin bushing, and insert flange on each thrust 
reverser half, with new, improved components.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
767-78A0089, dated July 19, 2001, which describes procedures for 
replacement of the existing deactivation pin, aft cascade pin bushing, 
and pin insert on each thrust reverser half, with new, improved 
components. Accomplishment of the actions specified in the service 
bulletin 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

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specified in the service bulletin described previously, except as 
discussed below.

Difference Between the Proposed AD and Alert Service Bulletin

    The service bulletin recommends incorporation of the specified 
actions at the earliest opportunity where facilities and manpower are 
available. 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 replacement. In light of all of these factors, 
the FAA finds a 24-month compliance time for accomplishing the required 
actions 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 90 airplanes of the affected design in the 
worldwide fleet. The FAA estimates that 26 airplanes of U.S. registry 
would be affected by this proposed AD, that it would take approximately 
12 work hours (6 work hours per engine) per airplane to accomplish the 
proposed actions, and that the average labor rate is $60 per work hour. 
Required parts would cost approximately $12,108 per airplane. Based on 
these figures, the cost impact of the proposed AD on U.S. operators is 
estimated to be $333,528, or $12,828 per airplane.
    The cost impact figure discussed above is 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. 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-268-AD.
    Applicability: Model 767-200 and -300 series airplanes powered 
by Pratt & Whitney JT9D series engines, 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 prevent failure of the thrust reverser deactivation pins, 
which could result in deployment of the thrust reverser in flight 
and consequent reduced controllability of the airplane, accomplish 
the following:

Replacement

    (a) Within 24 months after the effective date of this AD, 
replace the existing deactivation pin, pin bushing in the aft 
cascade mounting ring, and pin insert on each thrust reverser half, 
with new, improved components, according to Boeing Alert Service 
Bulletin 767-78A0089, dated July 19, 2001.

    Note 2: The new, improved insert flange and pin bushing does not 
preclude use of a deactivation pin having P/N 315T1604-2 or -5. 
However, use of deactivation pins having P/N 315T1604-2 or -5 may 
not prevent the thrust reversers from deploying in the event of a 
full powered deployment. Therefore, thrust reversers modified per 
this AD should be installed with the new, longer deactivation pins 
having P/N 315T1604-6, as specified in the applicable service 
bulletin.

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 9, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-28796 Filed 11-16-01; 8:45 am]
BILLING CODE 4910-13-U