[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Rules and Regulations]
[Pages 40812-40814]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20337]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-42-AD; Amendment 39-10680; AD 98-16-05]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300-600 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 all Airbus Model A300-600 series airplanes, that requires
inspections of the areas behind the scuff plates below the passenger/
crew doors and bulk cargo door to detect cracks and corrosion, and
repair, if necessary. This amendment also requires 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, this amendment provides for optional
terminating action for certain inspections. This amendment 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
this AD are intended to detect and correct such corrosion and fatigue
cracking, which could result in reduced structural integrity of the
door surroundings.
DATES: Effective September 4, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 4, 1998.
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: Norman B. Martenson, Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2110; 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 all Airbus Model A300-600 series
airplanes was published in the Federal Register on January 29, 1997 (62
FR 4211). That action proposed to require inspections of the lower door
surrounding structure to detect cracks and corrosion, and repair, if
necessary. That action also proposed to 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, that action proposed to provide for optional terminating
action for certain inspections.
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.
Clarification of Terminology
One commenter expresses no objection to the proposed rule, but
requests that certain terminology in the proposed AD be changed for the
sake of clarity. The commenter states that the title is not complete,
since it refers only to inspections of the lower door structure, while
inspection of the upper door corners is also required. The FAA concurs.
The FAA infers that the commenter is referring to the Summary section
of the proposed AD, which states that ``this proposal would require
inspections of the lower door surrounding structure.'' However, in all
other sections of the proposed AD, the area to be inspected is
described as ``the areas behind the scuff plates below the passenger/
crew doors and bulk cargo door,'' in accordance with procedures
described in Airbus Service Bulletin A300-53-6011, Revision 3, dated
February 4, 1991. To avoid confusion regarding the area to be inspected
for cracks and corrosion, the Summary section of the final rule has
been changed to correspond to the terminology used elsewhere throughout
the AD.
The same commenter requests that paragraphs (b) and (d) of the
proposed AD be changed to refer to the ``fail-safe ring and corner
strap,'' rather than the existing terminology of ``fail-safe ring and
corner doubler.'' The commenter states that the term ``corner strap''
is used in Airbus Service Bulletin A300-53-6022, dated February 4,
1991, and in other maintenance documents, rather than ``corner
doubler.'' The FAA does
[[Page 40813]]
not concur. The FAA has verified that the referenced service bulletin
uses the term ``corner doubler'' to identify the affected part.
Therefore, the usage of this terminology has been retained in the final
rule.
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 with the change described
previously. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Cost Impact
The FAA estimates that 35 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 700 work hours per
airplane to accomplish the required inspections (including access and
close-up), and that the average labor rate is $60 per work hour. Based
on these figures, the cost impact of the required AD on U.S. operators
is estimated to be $1,470,000, or $42,000 per airplane.
The cost impact figure 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.
Should an operator elect to accomplish the optional terminating
action that is provided by this AD action, it will take approximately
147 work hours to accomplish it, at an average labor rate of $60 per
work hour. The cost of required parts will be approximately $5,581 per
airplane. Based on these figures, the cost impact of the optional
terminating action will be $14,401 per airplane.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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
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
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:
98-16-05 Airbus: Amendment 39-10680. Docket 96-NM-42-AD.
Applicability: All Model A300-600 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 request approval for an
alternative method of compliance in accordance with paragraph (i) 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
A300-53-6011, Revision 3, dated February 4, 1991; at the time
specified in paragraph (a)(1), (a)(2), or (a)(3) 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 Modification 5382S6526 (for forward
doors) and Modification 5382D4741 (for all other doors) have been
accomplished prior to delivery of the airplane: Perform the initial
inspection within 9 years since date of manufacture, or within 1
year after the effective date of this AD, whichever occurs later.
(2) For airplanes on which Modification 5382S6526 (for forward
doors) and Modification 5382D4741 (for all other doors) have not
been accomplished; and on which the procedures described in Airbus
Service Information Letter (SIL) A300-53-033, Revision 2 (for all
doors), dated November 23, 1984, have been accomplished: Perform the
initial inspection within 5 years after accomplishment of the
procedures described in the SIL, or within 1 year after the
effective date of this AD, whichever occurs later.
(3) For airplanes on which Modification 5382S6526 (for forward
doors), Modification 5382D4741 (for all other doors), and the
procedures described in Airbus SIL A300-53-033, Revision 2, dated
November 23, 1984, have not been accomplished:
Perform the initial inspection within 4 years since date of
manufacture, or within 1 year after the effective date of this AD,
whichever occurs later.
(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
A300-53-6022, dated February 4, 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
door, and the aft passenger/crew doors, except 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.
(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 6,000 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 6,000 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 A300-53-6022, dated February
4, 1991. Thereafter, perform the repetitive inspections required by
paragraph (b) of this AD at the
[[Page 40814]]
applicable times specified in paragraphs (b)(1) and (b)(2) of this
AD.
(d) If corrosion is found during any inspection required by
paragraph (b) of this AD, prior to further flight, repair in
accordance with Airbus Service Bulletin A300-53-6022, dated February
4, 1991. Thereafter, perform the repetitive inspections required by
paragraph (b) of this AD at the applicable times specified in
paragraphs (d)(1) or (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 door: Inspect at intervals not to
exceed 5 years or 5,000 landings, whichever occurs first.
(2) For the forward passenger/crew doors and bulk cargo doors:
Inspect at intervals not to exceed 5 years.
(e) Perform an inspection 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 A300-53-6018,
Revision 1, dated April 29, 1992, and at the applicable time
specified in paragraph (e)(1), (e)(2), (e)(3), or (e)(4) of this AD.
(1) For the upper corners of the forward doors: Inspect prior to
the accumulation of 20,000 total landings, or within 2,000 landings
after the effective date of this AD, whichever occurs later.
(2) For the lower corners of the forward doors: Inspect prior to
the accumulation of 20,000 total landings, or within 4,000 landings
after the effective date of this AD, whichever occurs later.
(3) For the upper and lower corners of the mid doors: Inspect
prior to the accumulation of 20,000 total landings, or within 2,000
landings after the effective date of this AD, whichever occurs
later.
(4) For the upper and lower corners of the aft doors, and for
the parts underneath the corners of the upper door frames: Inspect
prior to the accumulation of 20,000 total landings, or within 4,000
landings after the effective date of this AD, whichever occurs
later.
(f) Repeat the inspections required by paragraph (e) of this AD
at the applicable times specified in paragraphs (f)(1), (f)(2),
(f)(3), (f)(4), and (f)(5).
(1) For the upper corners of the forward doors: Inspect at
intervals not to exceed 6,000 landings.
(2) For the lower corners of the forward doors: Inspect at
intervals not to exceed 10,000 landings.
(3) For the upper and lower corners of the mid and aft doors 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.
(4) For the upper and lower corners of the mid and aft doors 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.
(5) For the areas around the fasteners in the vicinity of
stringer 12 on the upper door frames of the aft doors 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) If any crack is found during any inspection required by
paragraph (e) or (f) of this AD: Prior to further flight, accomplish
the requirement of paragraph (g)(1) or (g)(2) of this AD, as
applicable.
(1) If any crack is found, and the crack can be eliminated using
the method specified in Airbus Service Bulletin A300-53-6018,
Revision 1, dated April 29, 1992: Prior to further flight, repair
the crack in accordance with that service bulletin.
(2) If any crack is found, and the crack cannot be eliminated
using the method specified in Airbus Service Bulletin A300-53-6018,
Revision 1, dated April 29, 1992: Prior to further flight, repair
the crack in accordance with a method approved by the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate.
(h) Modification of the passenger/crew door frames in accordance
with Airbus Service Bulletin A300-53-6002, Revision 3, dated
February 22, 1992, constitutes terminating action for the repetitive
inspections required by paragraph (f) of this AD.
(i) 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.
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 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the International Branch, ANM-116.
(j) 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.
(k) Except as provided by paragraph (g)(2) of this AD, the
actions shall be done in accordance with the following Airbus
service bulletins, which contain the specified list of effective
pages:
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Service bulletin referenced and Page number shown
date on page Revision level shown on page Date shown on page
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A300-53-6022, February 4, 1991. 1-15.............. Original..................... February 4, 1991.
A300-53-6002, Revision 3, 1-2, 56, 67-68.... 3............................ February 22, 1992.
February 22, 1992.
3-26, 31-55, 57-66 1............................ February 4, 1991.
27-30............. 2............................ May 6, 1991.
A300-53-6011, Revision 3, 1-17.............. 3............................ February 4, 1991.
February 4, 1991.
A300-53-6018, Revision 1, April 1, 3-4, 9-14, 17, 1............................ April 29, 1992.
29, 1992. 24, 31-34, 36, 50.
2, 5-8, 15-16, 18- Original..................... February 4, 1991.
23, 25-30, 35, 37-
49, 51-65.
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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.
Note 3: The subject of this AD is addressed in French
airworthiness directive 91-132-124(B), dated June 26, 1991, as
amended by a Correction, dated August 21, 1991.
(l) This amendment becomes effective on September 4, 1998.
Issued in Renton, Washington, on July 24, 1998.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-20337 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U