[Federal Register Volume 60, Number 207 (Thursday, October 26, 1995)]
[Proposed Rules]
[Pages 54820-54822]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-26558]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-156-AD]


Airworthiness Directives; Airbus Model A300, A300-600, A310, 
A330, and A340 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to all Airbus Model A300, 
A300-600, A310, A330, and A340 series airplanes, that currently 
requires an inspection of the sliding side windows in the cockpit to 
identify the part number of the windows. For airplanes on which a 
certain suspect window is installed, that AD also requires either 
deactivation of the sliding window defogging system; or installation of 
thermo-sensitive indicators, daily inspections of those indicators, and 
deactivation of the defogging system, if necessary; or replacement of 
the window with a serviceable window. The actions specified by the 
proposed AD are intended to prevent rupture of a cockpit sliding window 
and subsequent rapid decompression of the fuselage due to fracture of 
the window as a result of thermal stress created by overheating of the 
wires of the heating element in a localized area. This action would 
require replacement of certain windows with serviceable windows, which, 
when accomplished, terminates the requirements of the AD.

DATES: Comments must be received by December 6, 1995.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-156-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays.
    The service information referenced in the proposed rule may be 
obtained from 

[[Page 54821]]
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France. This information may be examined at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT: Charles D. Huber, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206) 
227-2589; fax (206) 227-1149.

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 notice may be changed in 
light of the comments received.
    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 notice must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 95-NM-156-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-103, Attention: Rules 
Docket No. 95-NM-156-AD, 1601 Lind Avenue SW., Renton, Washington 
98055-4056.

Discussion

    On January 19, 1995, the FAA issued AD 95-01-51, amendment 39-9125 
(60 FR 5564, January 30, 1995), applicable to all Airbus Model A300, 
A300-600, A310, A330, and A340 series airplanes, to require an 
inspection of the sliding side windows in the cockpit to identify the 
part number of the windows. For airplanes on which a certain suspect 
window is installed, that AD also requires either deactivation of the 
sliding window defogging system; or installation of thermo-sensitive 
indicators, daily inspections of those indicators, and deactivation of 
the defogging system, if necessary; or replacement of the window with a 
serviceable window. That action was prompted by reports of fracture of 
the sliding side window in the cockpit due to thermal stress created by 
overheating of the wires of the heating element in a localized area. 
The requirements of that AD are intended to prevent such fractures, 
which could lead to rupture of a cockpit sliding window and subsequent 
rapid decompression of the fuselage.
    AD 95-01-51 also contains a provision for the optional replacement 
of PPG Industries windows with serviceable windows manufactured by PPG 
Industries or by SPS. If accomplished, this replacement constitutes 
terminating action for the requirements of the AD. In the preamble to 
AD 95-01-51, the FAA indicated that the AD was considered to be interim 
action until final action was identified. The FAA has determined that 
``final action'' in addressing the unsafe condition that is the subject 
of this AD is the replacement of the suspect PPG Industries windows 
with serviceable windows (provided as an optional action in AD 95-01-
51).
    Additionally, since the issuance of AD 95-01-51, Airbus has issued 
All Operators Telex (AOT) 30-01, Revision 2, dated March 6, 1995, which 
describes procedures for an inspection of the left- and right-hand 
sliding side windows in the cockpit to identify the part number of the 
windows. For airplanes equipped with certain suspect windows 
manufactured by PPG Industries, the AOT also describes procedures for 
deactivation of the associated window defogging system; or installation 
of thermo-sensitive indicators, daily inspections of those indicators, 
and deactivation of the window defogging system, if necessary. The AOT 
also describes procedures for replacement of certain sliding windows 
with serviceable windows. Accomplishment of the replacement eliminates 
the need for the inspections, deactivation of the window defogging 
system, and installation of thermo-sensitive indicators. The Direction 
Generale de l'Aviation Civile (DGAC), which is the airworthiness 
authority for France, classified this AOT as mandatory and issued 
French airworthiness directives 94-285-173(B)R1 (for Model A300, A300-
600, and A310 series airplanes), 94-283-006(B)R1 (for Model A330 series 
airplanes), and 94-284-014(B)R1 (for Model A340 series airplanes), all 
dated April 12, 1995, in order to assure the continued airworthiness of 
these airplanes in France.
    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.
    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, the proposed AD would supersede AD 95-01-51 to 
continue to require an inspection of the sliding side windows in the 
cockpit to identify the part number of the windows. For airplanes on 
which a certain suspect window is installed, the proposed AD also would 
continue to require either deactivation of the sliding window defogging 
system; or installation of thermo-sensitive indicators, daily 
inspections of those indicators, and deactivation of the defogging 
system, if necessary. The proposed AD also would require the eventual 
replacement of suspect windows with serviceable windows. Replacement of 
the windows would constitute terminating action for the requirements of 
the AD. The actions would be required to be accomplished in accordance 
with the AOT described previously.
    There are approximately 66 Model A300, A300-600, and A310 series 
airplanes of U.S. registry that would be affected by this proposed AD. 
(Currently, there are no Model A330 or A340 series airplanes on the 
U.S. Register.)
    The inspections that are currently required by AD 95-01-51 take 
approximately 1 work hour per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the total cost 
impact on U.S. operators of the actions currently required is estimated 
to be $3,960, or $60 per airplane.
    The replacement of the windows, which is proposed in this new AD 
action, would take approximately 7 

[[Page 54822]]
work hours per airplane to accomplish, at an average labor rate of $60 
per work hour. Required parts would be provided by the manufacturer at 
no cost to operators. Based on these figures, the total cost impact on 
U.S. operators of the proposed requirements of this AD is estimated to 
be $27,720, or $420 per airplane.
    The total cost impact figures discussed above are based on 
assumptions that no operator has yet accomplished any of the current or 
proposed requirements of this AD action, and that no operator would 
accomplish those actions in the future if this AD were not adopted.
    The regulations proposed herein would 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 
proposal would not have sufficient federalism implications to warrant 
the preparation of a Federalism Assessment.
    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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9125 (60 FR 
5564, January 1, 1995), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 95-NM-156-AD. Supersedes AD 95-01-51, 
Amendment 39-9125.

    Applicability: All Model A300, A300-600, A310, A330, and A340 
series airplanes, 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 use the authority 
provided in paragraph (e) of this AD to request approval from the 
FAA. This approval may address either no action, if the current 
configuration eliminates the unsafe condition; or different actions 
necessary to address the unsafe condition described in this AD. Such 
a request should include an assessment of the effect of the changed 
configuration on the unsafe condition addressed by this AD. In no 
case does the presence of any modification, alteration, or repair 
remove any airplane from the applicability of this AD.

    Compliance: Required as indicated, unless accomplished 
previously. To prevent rupture of a cockpit sliding window and 
subsequent rapid decompression of the fuselage due to fracture of 
the window as a result of thermal stress created by overheating of 
the wires of the heating element in a localized area, accomplish the 
following:
    (a) Within 7 days after February 14, 1995 (the effective date of 
AD 95-01-51, amendment 39-9125), perform an inspection of the left- 
and right-hand sliding side windows in the cockpit to identify the 
part number (P/N) of those windows, in accordance with paragraph 4.1 
of Airbus All Operators Telex (AOT) 30-01, dated December 22, 1994; 
or Revision 2, dated March 6, 1995.
    (b) If no window manufactured by PPG Industries having P/N 
NP175202-1 (left-hand side) or NP175202-2 (right-hand side) is 
installed, no further action is required by this AD.
    (c) If any window manufactured by PPG Industries having P/N NP 
175202-1 (left-hand side) or NP 175202-2 (right-hand side) is 
installed, prior to further flight, accomplish either paragraph 
(c)(1) or (c)(2) of this AD in accordance with Airbus AOT 30-01, 
dated December 22, 1994; or Revision 2, dated March 6, 1995.
    (1) Deactivate the associated sliding window defogging system in 
accordance with the procedures specified in paragraph 4.2.2 of the 
AOT. The defogging system may remain deactivated until the window is 
replaced in accordance with paragraph (d) of this AD. Or

    Note 2: This AD may permit the defogging system to be 
deactivated for a longer time than is specified in the Master 
Minimum Equipment List (MMEL). In any case, the provisions of this 
AD prevail.

    (2) Install thermo-sensitive indicators in two areas of the 
sliding side window (left- and right-hand sides) in accordance with 
the procedures specified in paragraph 4.3 of the AOT. Thereafter, 
perform a daily inspection of the indicators to determine if the 60-
degree segment of any indicator turns from light grey to black, in 
accordance with the procedures specified in paragraph 4.3 of the 
AOT. If any indicator turns black, prior to further flight, 
deactivate the associated sliding window defogging system in 
accordance with paragraph (c)(1) of this AD.
    (d) Within 90 days after the effective date of this AD, replace 
any PPG Industries window having part number (P/N) NP 175202-1 
(left-hand side) or NP 175202-2 (right-hand side) with a serviceable 
window manufactured by PPG Industries or by SPS, as listed in 
paragraph 5.1 of AOT 30-01, dated December 22, 1994; or paragraphs 
5.2.1 (PPG Industries windows) and 5.2.2 (SPS windows) of AOT 30-01, 
Revision 2, dated March 6, 1995. Accomplish the replacement in 
accordance with the procedures specified in AOT 30-01, dated 
December 22, 1994, or Revision 2, dated March 6, 1995. After such 
replacement, no further action is required by this AD.
    (e) 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 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Standardization Branch, ANM-113.

    (f) 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 October 20, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-26558 Filed 10-25-95; 8:45 am]
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