[Federal Register Volume 62, Number 19 (Wednesday, January 29, 1997)]
[Proposed Rules]
[Pages 4213-4217]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-2220]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-NM-43-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 4214]]
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 all Airbus Model A300 series
airplanes. This proposal would require inspections of the lower door
surrounding structure to detect cracks and corrosion, and repair, if
necessary. This proposal also would require inspections to detect
cracking of the holes of the corner doublers, the fail-safe ring, and
the door frames of the door structures; and repair, if necessary. This
proposal would require modification of the passenger/crew door frames,
which, when accomplished, terminates certain inspections. This proposal
is prompted by reports indicating that corrosion was found behind the
scuff plates at exit and cargo doors, and fatigue cracks originated
from certain fastener holes located in adjacent structure. The actions
specified by the proposed AD are intended to detect and correct such
corrosion and fatigue cracking, which could result in reduced
structural integrity of the door surroundings.
DATES: Comments must be received by March 10, 1997.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 96-NM-43-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.
The service information referenced in the proposed rule may be
obtained from 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 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 96-NM-43-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. 96-NM-43-AD, 1601 Lind Avenue, SW., Renton, Washington
98055-4056.
Discussion
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, has notified the FAA that an unsafe
condition may exist on all Airbus Model A300 series airplanes. The DGAC
advises that it received reports indicating that corrosion was found
behind the scuff plates at passenger/crew doors, emergency exits, and
the bulk cargo door. The DGAC also advises that results of structural
fatigue testing have revealed that cracks were found on the corner
doublers of the forward, mid, and aft passenger/crew door frames; and,
after various simulated flights, on the fail-safe ring and frames 14
and 16A of the forward passenger/crew door. After 50,000 simulated
flights, cracks measuring between 8.0 mm and 109.0 mm were found on the
forward door frames and fail-safe ring. On the mid door frame, a 53.0
mm crack was found after 60,493 simulated flights. A crack which
measured 32.0 mm was found on the aft door frame after 106,000
simulated flights. In all cases, the cracks originated at the fastener
holes. In addition, cracks originating from corner doubler edges were
found at the aft passenger/crew doors.
Such corrosion and fatigue cracking, if not detected and corrected,
could result in reduced structural integrity of the door surroundings.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A300-53-204, Revision 6, dated
October 11, 1993, which describes procedures for a one-time inspection
to detect cracks and corrosion in the areas behind the scuff plates at
passenger/crew doors, emergency exits, and the bulk cargo door, and
repair, if necessary. Airbus also has issued Service Bulletin A300-53-
233, Revision 1, dated April 18, 1991, which describes procedures for
corresponding repetitive inspections in these areas, and repair, if
necessary.
In addition, Airbus has issued Service Bulletin A300-53-227,
Revision 1, dated April 29, 1992. This service bulletin describes
procedures for repetitive inspections to detect cracking of the holes
of the corner doublers, the fail-safe ring, and the door frames at the
left- and right-hand forward, mid, and aft passenger/crew door
structures; and repair, if necessary.
Airbus also has issued Service Bulletin A300-53-192, Revision 7,
dated July 13, 1992, which describes procedures for modification of the
passenger/crew door frames. This modification consists of performing
cold expansion procedures on the fastener holes in door frames, corner
doublers, and fail-safe rings; and installing oversized Hi-Lok
fasteners and additional steel doublers at door frame corners, where
necessary, to improve the fatigue life of the corner doublers, fail-
safe rings, and door frames. Accomplishment of the modification
eliminates the need for the repetitive inspections specified in Airbus
Service Bulletin A300-53-227.
The DGAC classified the inspection service bulletins as mandatory
and issued French airworthiness directive (CN) 91-132-124(B), dated
June 26, 1991, as amended by a Correction, dated August 21, 1991, in
order to assure the continued airworthiness of these airplanes in
France. (The DGAC did not classify the modification service bulletin as
mandatory.)
FAA's Conclusions
This airplane model is manufactured in France and is 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
[[Page 4215]]
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.
Explanation of Requirements of Proposed Rule
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 require inspections of the
lower door surrounding structure to detect cracks and corrosion, and
repair, if necessary. The proposed AD also would require inspections to
detect cracking of the holes of the corner doublers, the fail-safe
ring, and the door frames of the door structures; and repair, if
necessary. In addition, the proposed AD would require modification of
the passenger/crew door frames, which, when accomplished, constitutes
terminating action for certain inspections. The actions would be
required to be accomplished in accordance with the service bulletins
described previously.
Differences Between Proposed Rule and Parallel French CN
Operators should note that the French CN does not mandate
modification of the passenger/crew door frames. However, the FAA finds
that, since the design of Model A300 series airplanes is not damage
tolerant, accomplishment of the modification described in Airbus
Service Bulletin A300-53-192 must be required.
Additionally, the FAA considers that long term continued
operational safety will be better assured by actual modification of the
airframe to remove the source of the problem, rather than by repetitive
inspections. Long term inspections may not be providing the degree of
safety assurance necessary for the transport airplane fleet. This has
led the FAA to consider placing less emphasis on special procedures and
more emphasis on design improvements. The proposed modification
requirement is in consonance with this consideration.
Cost Impact
The FAA estimates that 4 airplanes of U.S. registry would be
affected by this proposed AD.
It would take approximately 700 work hours per airplane to
accomplish the proposed inspections, and that the average labor rate is
$60 per work hour. Based on these figures, the cost impact of the
proposed inspections on U.S. operators is estimated to be $168,000, or
$42,000 per airplane.
The FAA estimates that it would take approximately 330 work hours
per airplane to accomplish the proposed modification, and that the
average labor rate is $60 per work hour. Required parts would cost
approximately $1,055 per airplane. Based on these figures, the cost
impact of the proposed modification on U.S. operators is estimated to
be $83,420, or $20,855 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 AD were not adopted.
Regulatory Impact
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 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus: Docket 96-NM-43-AD.
Applicability: All Model A300 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
otherwise 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 (h) 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 detect and correct corrosion behind the scuff plates at exit
and cargo doors, and fatigue cracking in certain fastener holes
located in adjacent structure, which could result in reduced
structural integrity of the door surroundings, accomplish the
following:
(a) Perform an initial inspection of the areas behind the scuff
plates below the passenger/crew doors and bulk cargo door to detect
cracks and corrosion, in accordance with Airbus Service Bulletin
A300-53-204, Revision 6, dated October 11, 1993; at the applicable
time specified in paragraph (a)(1), (a)(2), (a)(3), or (a)(4) of
this AD. If any crack or corrosion is found during this inspection,
prior to further flight, repair in accordance with the service
bulletin. Accomplishment of this inspection is not required for the
mid and aft passenger/crew doors if a steel doubler that covers the
entire inspection area is installed.
(1) For airplanes on which Modifications 5382S6526 (for forward
doors), 3690S4613 (for forward doors), and 5382D4741 (for all other
doors) have been accomplished prior to delivery of the airplane:
Perform the initial inspection within 9 years since manufacture, or
within 1 year after the effective date of this AD, whichever occurs
later.
(2) For airplanes on which the procedures described in Airbus
Service Information Letter (SIL) A300-53-033, Revision 2 (for all
doors), dated November 23, 1984; or Airbus Service Bulletin A300-53-
169 (for forward doors), Revision 2, dated May 14, 1985; have been
accomplished: Perform the initial inspection within 5 years after
accomplishment of the SIL or the service bulletin, or within 1 year
after the effective date of this AD, whichever occurs later.
(3) For airplanes on which the procedures described in Airbus
Service Bulletin A300-53-116 (for all doors), Revision 4, dated June
30, 1983, have been accomplished: Perform the initial inspection
within 2 years after accomplishment of the procedures in accordance
with that service bulletin, or
[[Page 4216]]
within 1 year after the effective date of this AD, whichever occurs
later.
(4) For airplanes on which Modifications 5382S6526 (for forward
doors), 3690S4613 (for forward doors), and 5382D4741 (for all other
doors); and the procedures described in Airbus Service Bulletin
A300-53-116, Revision 4, dated June 30, 1983; or Service Information
Letter (SIL) A300-53-033, Revision 2, dated November 23, 1984; have
not been accomplished: Perform the initial inspection within 1 year
after the effective date of this AD.
(b) Perform repetitive inspections of the areas behind the scuff
plates below the passenger/crew doors and bulk cargo door to detect
cracks and corrosion, in accordance with Airbus Service Bulletin
A300-53-233, Revision 1, dated April 18, 1991, at the applicable
times specified in paragraphs (b)(1) and (b)(2) of this AD.
Accomplishment of these inspections is not required for the mid and
aft passenger/crew doors if a steel doubler that covers the entire
inspection area is installed.
(1) For the forward and mid passenger/crew doors, the bulk cargo
doors, the emergency exits, and the aft passenger/crew doors, except
for the upper and lower edges of the fail-safe ring and the upper
edges of the corner doubler: Perform the first inspection within 5
years after accomplishing the inspection required by paragraph (a)
of this AD; and repeat the inspection thereafter at intervals not to
exceed 5 years following the immediately preceding inspection.
(2) For the upper and lower edges of the fail-safe ring and the
upper edges of the corner doubler of the aft passenger/crew doors:
Perform the first inspection within 5 years or 10,000 landings after
accomplishing the inspection required by paragraph (a) of this AD,
whichever occurs first; and repeat the inspection thereafter at
intervals not to exceed 5 years or 10,000 landings, whichever occurs
first.
(c) If any crack is found during any inspection required by
paragraph (b) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A300-53-233, Revision 1,
dated April 18, 1991. Thereafter, perform the repetitive inspections
required by paragraph (b) of this AD at the applicable times
specified in paragraphs (b)(1) and (b)(2) of this AD.
(d) If any corrosion is found during any inspection required by
paragraph (b) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A300-53-233, Revision 1,
dated April 18, 1991. Thereafter, perform the repetitive inspections
required by paragraph (b) of this AD at the applicable times
specified in paragraphs (d)(1) and (d)(2) of this AD.
(1) For the upper and lower edges of the fail-safe ring and the
upper edges of the corner doubler of the aft passenger/crew doors,
and for the mid passenger/crew doors: Inspect at intervals not to
exceed 5 years or 8,000 landings, whichever occurs first.
(2) For the forward passenger/crew doors, bulk cargo door, and
emergency exits: Inspect at intervals not to exceed 5 years.
(e) Perform inspections to detect cracking of the holes of the
corner doublers, the fail-safe ring, and the door frames of the
left- and right-hand forward, mid, and aft passenger/crew door
structures, in accordance with Airbus Service Bulletin A300-53-227,
Revision 1, dated April 29, 1992. Perform the inspections at the
times specified in paragraphs (e)(1), (e)(2), and (e)(3) of this AD,
as applicable. If any cracking is found, prior to further flight,
repair in accordance with the service bulletin; or, if cracks cannot
be eliminated in accordance with the service bulletin, repair in
accordance with a method approved by the Manager, Standardization
Branch, ANM-113, FAA, Transport Airplane Directorate.
(1) Except as provided by paragraph (e)(2) of this AD, for the
left- and right-hand forward and mid passenger/crew door structures
of all airplanes: Inspect at the time specified in paragraph
(e)(1)(i), (e)(1)(ii), (e)(1)(iii), or (e)(1)(iv) of this AD, as
applicable.
(i) For airplanes that have accumulated less than 20,000 total
landings as of the effective date of this AD: Inspect prior to the
accumulation of 20,000 total landings, or within 1,250 landings
after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 20,000 total landings
or more, but less than 21,000 landings as of the effective date of
this AD: Inspect prior to the accumulation of 21,000 total landings,
or within 1,000 landings after the effective date of this AD,
whichever occurs later.
(iii) For airplanes that have accumulated 21,000 total landings
or more, but less than 22,000 landings as of the effective date of
this AD: Inspect prior to the accumulation of 22,000 total landings,
or within 500 landings after the effective date of this AD,
whichever occurs later.
(iv) For airplanes that have accumulated 22,000 total landings
or more as of the effective date of this AD: Inspect within 250
landings after the effective date of this AD.
(2) For the left-hand mid passenger/crew door structures of
Model A300 C4 and F4 series airplanes: Inspect at the time specified
in paragraph (e)(2)(i), (e)(2)(ii), (e)(2)(iii), or (e)(2)(iv) of
this AD, as applicable.
(i) For airplanes that have accumulated less than 12,000 total
landings as of the effective date of this AD: Inspect prior to the
accumulation of 12,000 total landings, or within 1,250 landings
after the effective date of this AD, whichever occurs later.
(ii) For airplanes that have accumulated 12,000 total landings
or more, but less than 13,000 landings as of the effective date of
this AD: Inspect prior to the accumulation of 13,000 total landings,
or within 1,000 landings after the effective date of this AD,
whichever occurs later.
(iii) For airplanes that have accumulated 13,000 total landings
or more, but less than 14,000 landings as of the effective date of
this AD: Inspect prior to the accumulation of 14,000 total landings,
or within 500 landings after the effective date of this AD,
whichever occurs later.
(iv) For airplanes that have accumulated 14,000 total landings
or more as of the effective date of this AD: Inspect within 250
landings after the effective date of this AD.
(3) For the left- and right-hand aft passenger/crew door
structures of all airplanes: Inspect prior to the accumulation of
24,000 total landings, or within 250 landings after the effective
date of this AD, whichever occurs later.
(f) Repeat the inspections required by paragraph (e) of this AD
at the times specified in paragraphs (f)(1), (f)(2), (f)(3), (f)(4),
(f)(5), (f)(6), (f)(7), (f)(8), (f)(9), and (f)(10), as applicable,
until the modification required by paragraph (g) of this AD is
accomplished.
(1) For the forward passenger/crew door structure of airplanes
on which Airbus Modification No. 1282/S1862 has not been
accomplished: Inspect at the intervals specified in paragraphs
(f)(1)(i) and (f)(1)(ii), as applicable.
(i) For the upper corners of the door structure: At intervals
not to exceed 4,000 landings.
(ii) For the lower corners of the door structure: At intervals
not to exceed 7,500 landings.
(2) For the forward passenger/crew door structure of airplanes
on which Airbus Modification No. 1282/S1862 has been accomplished:
Inspect at the intervals specified in paragraphs (f)(2)(i) and
(f)(2)(ii), as applicable.
(i) For the upper corners of the door structure: At intervals
not to exceed 6,000 landings.
(ii) For the lower corners of the door structure: At intervals
not to exceed 10,000 landings.
(3) For the forward passenger/crew door structure of the
airplane having manufacturer's serial number 063, on which Airbus
Modification No. 1282/S1862 has been accomplished partially: Inspect
at the intervals specified in paragraph (f)(3)(i) or (f)(3)(ii), as
applicable.
(i) For the upper corners of the door structure: At intervals
not to exceed 4,000 landings.
(ii) For the lower corners of the door structure: At intervals
not to exceed 7,500 landings.
(4) For the left- and right-hand mid passenger/crew door
structure on Model A300 B1, B2, and B4 series airplanes; and for the
right-hand mid passenger/crew door structure on Model A300 C4 and F4
series airplanes; on which an inspection required by paragraph (e)
of this AD was accomplished using a Roto test technique: Inspect at
intervals not to exceed 8,000 landings.
(5) For the left- and right-hand mid passenger/crew door
structure on Model A300 B1, B2, and B4 series airplanes; and for the
right-hand mid passenger/crew door structure on Model A300 C4 and F4
series airplanes; on which an inspection required by paragraph (e)
of this AD was accomplished using an X-ray technique: Inspect at
intervals not to exceed 3,500 landings.
(6) For the left-hand mid passenger/crew door structure on Model
A300 C4 and F4 series airplanes on which an inspection required by
paragraph (e) of this AD was accomplished using a Roto test
technique: Inspect at intervals not to exceed 5,200 landings.
(7) For the left-hand mid passenger/crew door structure on Model
A300 C4 and F4
[[Page 4217]]
series airplanes on which an inspection required by paragraph (e) of
this AD was accomplished using an X-ray technique: Inspect at
intervals not to exceed 2,300 landings.
(8) For the aft passenger/crew door structure on which an
inspection required by paragraph (e) of this AD was accomplished
using a Roto test technique: Inspect at intervals not to exceed
8,000 landings.
(9) For the aft passenger/crew door structure on which an
inspection required by paragraph (e) of this AD was accomplished
using an X-ray technique: Inspect at intervals not to exceed 3,500
landings.
(10) For the areas around the fasteners in the vicinity of
stringer 12 on the aft passenger/crew door structure on which an
inspection required by paragraph (e) of this AD was accomplished
using a visual technique: Inspect at intervals not to exceed 6,900
landings.
(g) Prior to the accumulation of 20,000 total landings, or
within 1 year after the effective date of this AD, whichever occurs
later: Modify the passenger/crew door structures in accordance with
Airbus Service Bulletin A300-53-192, Revision 7, dated July 13,
1992. Accomplishment of this modification constitutes terminating
action for the repetitive inspections required by paragraph (f) of
this AD.
(h) 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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(i) 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 January 23, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-2220 Filed 1-28-97; 8:45 am]
BILLING CODE 4910-13-P
