AD 2003-14-01

[Federal Register Volume 68, Number 132 (Thursday, July 10, 2003)]
[Rules and Regulations]
[Pages 41056-41059]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-17313]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-154-AD; Amendment 39-13220; AD 2003-14-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2, A300 B4, A300 B4-
600, A300 B4-600R, A300 F4-600R, A310, A330, and A340 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 Airbus airplanes, that requires repetitive 
inspections for foreign objects between the slider and the girt bar 
attachment fittings of the

[[Page 41057]]

emergency escape slides; a one-time inspection for correct adjustment 
of the slide release mechanism and the girt bar attachment fittings, 
which would terminate the repetitive inspections; a one-time test for 
correct extension of the girt bar through the sliders; and corrective 
action, if necessary. The actions specified by this AD are intended to 
prevent failure of an emergency escape slide, which could result in a 
delayed evacuation in an emergency and consequent injury to passengers 
or crew. This action is intended to address the identified unsafe 
condition.

DATES: Effective August 14, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 14, 2003.

ADDRESSES: The service information referenced in this AD may be 
obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France. This information may be examined at the Federal 
Aviation Administration (FAA), Transport Airplane Directorate, Rules 
Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
the Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain Airbus airplanes was 
published as a supplemental notice of proposed rulemaking (NPRM) in the 
Federal Register on January 3, 2003 (68 FR 315). That action proposed 
to require repetitive inspections for foreign objects between the 
slider and the girt bar attachment fittings of the emergency escape 
slides; a one-time inspection for correct adjustment of the slide 
release mechanism and the girt bar attachment fittings, which would 
terminate the repetitive inspections; a one-time test for correct 
extension of the girt bar through the sliders; and corrective action, 
if necessary.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Request To Revise Compliance Interval

    Two commenters request that the proposed AD be revised to change 
the repetitive interval for inspecting the emergency exit doors for 
foreign objects. The commenters request that the inspection be required 
not at the proposed 7-day interval, but only when the door is removed 
or maintenance is done on the door or slide assembly. The commenters 
assert that the emergency exit doors are not regularly opened and do 
not collect debris at the same rate as passenger doors, and that the 
interior side wall panels of the emergency doors prevent debris from 
being introduced into the slide release mechanism. The commenters 
suggest that opening the emergency exit doors every 7 days could 
accelerate wear of the slider and girt bar attach mechanisms and could 
increase the amount of dirt, debris, and corrosion introduced into the 
door mechanism. The commenters further suggest that the visual 
inspection be included in the aircraft maintenance manual upon 
installation and other relevant maintenance procedures regarding the 
emergency exit doors.
    The FAA does not agree with the request. The girt bar, sliders, and 
attachment fittings of the emergecy and passengers doors are identical 
in design and are located close to the floor. The girt bars of all 
doors are subject to the same risk of being affected by debris--
regardless of how often the doors are opened--because of the open 
access to the cabin; debris can still reach and affect the girt bar of 
a closed door. In addition, according to the manufacturer, there is no 
risk of increased wear on the moving components due to frequent use. 
Further, the inspection for the emergency doors can be done quickly. No 
change to the final rule is necessary regarding this issue.

Request To Delay Issuance of AD Pending Revised Procedures

    Two commenters request that the FAA delay issuing the AD until an 
appropriate measuring device can be developed to measure the gap 
between the sliders and the girt bar. The commenters state that the 
mechanism is poorly accessible and the measurement procedure requires 
special skills, tooling, and training to be accomplished consistently. 
They add that typical measuring tools are impractical due to the 
mechanism's close proximity to the fuselage door cutout, and the tool 
depicted in Figure 2, sheet 4, of the service bulletin referenced in 
the supplemental NPRM is difficult to manufacture with the appropriate 
dimensional indications.
    However, another commenter notes that, because operators had 
difficulties following the procedures to perform the measurements, 
Airbus has revised the service information to add work instructions and 
clarify the procedures to inspect and test the release mechanism attach 
fittings.
    The FAA does not agree with the request to delay issuance of the 
AD. The service bulletin procedures for checking the slide release 
mechanism can be complex. As a result, Airbus has improved the 
instructions in the revised service bulletins (which were described in 
the supplemental NPRM). Furthermore, the measuring tool shown in Figure 
2, sheet 4, of the service bulletins is provided as a typical example 
of a tool to be used for measuring the extension of the sliders over 
the girt bar; that tool can be easily made from any sheet of aluminum 
and is not considered a specific tool. In addition, no specialized 
training is necessary to perform this measurement. No change to the 
final rule is necessary regarding this issue.

Conclusion

    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 as proposed.

Changes to 14 CFR Part 39/Effect on the AD

    On July 10, 2002, the FAA issued a new version of 14 CFR part 39 
(67 FR 47997, July 22, 2002), which governs the FAA's airworthiness 
directives system. The regulation now includes material that relates to 
altered products, special flight permits, and alternative methods of 
compliance. However, for clarity and consistency in this final rule, we 
have retained the language of the supplemental NPRM regarding that 
material.

Cost Impact

    The FAA estimates that there are 103 Model A300 B2, A300 B4, A300 
B4-600, A300 B4-600R, A300 F4-600R, A310, and A330 series airplanes of 
U.S. registry that will be affected by this AD. There are no Model A340 
series airplanes currently on the U.S. Register; however, if an 
affected Model A340 series airplane is imported and placed on the U.S. 
Register in the future, the cost impact would be the same as for the 
remaining affected airplanes, as described below.
    It will take approximately 2 work hours per airplane to inspect for 
foreign

[[Page 41058]]

objects between the slider and the girt bar attachment fittings, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this inspection on U.S. operators is estimated to be 
$12,360, or $120 per airplane, per inspection cycle.
    It will take approximately 4 work hours per airplane to determine 
whether the slide mechanism and girt bar attachment fittings are 
adjusted correctly, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of this inspection on U.S. 
operators is estimated to be $24,720, or $240 per airplane.
    It will take approximately 4 work hours per airplane to determine 
whether the girt bar extends through the sliders correctly, at an 
average labor rate of $60 per work hour. Based on these figures, the 
cost impact of this inspection on U.S. operators is estimated to be 
$24,720, or $240 per airplane.
    The cost impact figures 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 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 adopted herein will 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 final rule does not have federalism 
implications under Executive Order 13132.
    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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-14-01 Airbus: Amendment 39-13220. Docket 2001-NM-154-AD.

    Applicability: The following airplanes, certificated in any 
category:

                         Table 1.--Applicability
------------------------------------------------------------------------
                                            Listed in Airbus Service
               Model--                             Bulletin--
------------------------------------------------------------------------
A300 B2 and A300 B4 series airplanes.  A300-52-0174, Revision 01, dated
                                        August 23, 2002.
A300 B4-600, A300 B4-600R, and A300    A300-52-6062, Revision 01, dated
 F4-600R series airplanes.              August 23, 2002.
A310 series airplanes................  A310-52-2066, Revision 01, dated
                                        August 23, 2002.
A330 series airplanes................  A330-52-3064, Revision 01, dated
                                        June 12, 2002.
A340 series airplanes................  A340-52-4076, Revision 01, dated
                                        June 12, 2002.
------------------------------------------------------------------------


    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 (d) 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 an emergency escape slide, which could 
result in a delayed evacuation in an emergency and consequent injury 
to passengers or crew, accomplish the following:

Repetitive Inspections for Foreign Objects

    (a) At the applicable time specified in paragraph (a)(1) or 
(a)(2) of this AD: Perform a general visual inspection for foreign 
objects between the slider and the girt bar attachment fittings of 
the emergency escape slides according to the applicable service 
bulletin listed in Table 2 of this AD. Repeat the inspection at 
least every 7 days until the actions required by paragraph (b) of 
this AD are done. If any foreign object is found during any 
inspection required by paragraph (a) of this AD: Before further 
flight, remove the object and ensure that the girt bar attachment 
fittings are clean, according to the applicable service bulletin. 
Table 2 follows:

       Table 2.--Service Bulletin References for Required Actions
------------------------------------------------------------------------
                                       Do the actions in accordance with
             For model--                   Airbus Service Bulletin--
------------------------------------------------------------------------
A300 B2 and A300 B4 series airplanes.  A300-52-0174, Revision 01, dated
                                        August 23, 2002.
A300 B4-600, A300 B4-600R, and A300    A300-52-6062, Revision 01, dated
 F4-600R series airplanes.              August 23, 2002.
A310 series airplanes................  A310-52-2066, Revision 01, dated
                                        August 23, 2002.
A330 series airplanes................  A330-52-3064, Revision 01, dated
                                        June 12, 2002.
A340 series airplanes................  A340-52-4076, Revision 01, dated
                                        June 12, 2002.
------------------------------------------------------------------------


[[Page 41059]]

    (1) For Model A330 and A340 series airplanes: Inspect within 7 
days after the effective date of this AD.
    (2) For Model A300, A300-600, and A310 series airplanes: Inspect 
within 550 flight hours after the effective date of this AD.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as: ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made from within 
touching distance unless otherwise specified. A mirror may be 
necessary to enhance visual access to all exposed surfaces in the 
inspection area. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or droplight and may require removing or opening access 
panels or doors. Stands, ladders, or platforms may be required to 
gain proximity to the area being checked.''

One-Time Inspection of Slide Release Mechanism and Girt Bar Attachment 
Fittings

    (b) Within 18 months after the effective date of this AD, 
perform a one-time general visual inspection for correct adjustment 
of the emergency escape slide release mechanism and the girt bar 
attachment fittings according to the service bulletin listed in 
Table 2 of this AD, as applicable. If the slide mechanism or girt 
bar attachment fittings are not adjusted correctly: Before further 
flight, adjust them according to the applicable service bulletin. 
Accomplishment of this inspection and any required corrective 
actions terminates the repetitive inspections required by paragraph 
(a) of this AD.

One-Time Inspection of Girt Bar Attachment Fittings

    (c) Within 18 months after the effective date of this AD, 
perform a one-time general visual inspection for correct extension 
of the emergency escape slide girt bar through the sliders, 
according to the service bulletin listed in Table 2 of this AD, as 
applicable. If the girt bar does not extend correctly: Before 
further flight, rework the girt bar or replace the girt bar assembly 
with a new assembly, according to the applicable service bulletin.

Alternative Methods of Compliance

    (d) 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, International Branch, ANM-116, 
Transport Airplane Directorate, FAA. Operators shall submit their 
requests through an appropriate FAA Principal Maintenance Inspector, 
who may add comments and then send it to the Manager, International 
Branch, ANM-116.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    (e) 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.

Incorporation by Reference

    (f) The actions must be done in accordance with Airbus Service 
Bulletin A300-52-0174, Revision 01, dated August 23, 2002; Airbus 
Service Bulletin A300-52-6062, Revision 01, dated August 23, 2002; 
Airbus Service Bulletin A310-52-2066, Revision 01, dated August 23, 
2002; Airbus Service Bulletin A330-52-3064, Revision 01, dated June 
12, 2002; or Airbus Service Bulletin A340-52-4076, Revision 01, 
dated June 12, 2002; as applicable. This incorporation by reference 
was approved by the Director of the Federal Register in accordance 
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from 
Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France. Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.

Effective Date

    (g) This amendment becomes effective on August 14, 2003.

    Note 4: The subject of this AD is addressed in French 
airworthiness directives 2002-296(B) and 2002-297(B), both dated 
June 12, 2002; and 2002-525(B), dated October 16, 2002.


    Issued in Renton, Washington, on June 30, 2003.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-17313 Filed 7-9-03; 8:45 am]
BILLING CODE 4910-13-P