[Federal Register Volume 63, Number 147 (Friday, July 31, 1998)]
[Rules and Regulations]
[Pages 40819-40821]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-20338]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-44-AD; Amendment 39-10682; AD 98-16-06]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 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 A310 series airplanes, that requires
inspections of the lower door surrounding structure 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 between 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 A310 series
airplanes was published in the Federal Register on January 29, 1997 (62
FR 4208). 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 also provides 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 single comment received.
Request to Mandate Optional Terminating Action
One commenter supports the proposed AD, but states that the FAA
should not allow operators to forego accomplishment of the terminating
action in lieu of repetitive inspections. The commenter states that
allowing the terminating action to be optional will ``allow airplanes
to operate that have cracks in the door frames that will be more
subject to failure in the event of an accident.'' Additionally, the
commenter notes that accident history has shown that there is already a
significant problem with the emergency operation of doors following
minor fuselage deformation, even though this is a requirement under
section 25.783(c) of the Federal Aviation Regulations [14 CFR
25.783(c)].
The FAA does not concur with the request to mandate the terminating
action. As stated in the preamble to the NPRM, the FAA considers
certain criteria in allowing repetitive inspections of the affected
area to be permitted to continue, and has determined that, in this
case, mandating the terminating action is not necessary in order to
adequately address the identified unsafe condition. The FAA has
determined that the inspection intervals required by the AD were
established to detect any cracking before it becomes critical to the
airplane structure. Additionally, even if small cracks exist that are
not detected by the inspections at the intervals required by this AD,
the cracks will not adversely affect the structure of the door under
ultimate loads, and such cracking is unlikely to result in interference
with the operation of emergency exits. Therefore, no change to the
final rule is necessary.
Explanation of Change Made to This Final Rule
Paragraphs (b), (c), and (d) of the final rule have been revised to
cite Revision 02 of Airbus Service Bulletin A310-53-2041, dated July 2,
1996, for accomplishment of certain actions. Revision 02 contains no
substantive differences from Revision 1 of the service bulletin
(Revision 1 was cited as the appropriate source of service information
in the proposed AD). However, Revision 02 contains an additional
description of the inspections required by paragraph (b) of the AD. A
``NOTE'' has been added to the final rule to give credit to operators
that may have previously accomplished the required actions in
accordance with Revision 1 of the service bulletin.
Conclusion
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change previously
described. The FAA has determined that this change will neither
increase the economic burden on any
[[Page 40820]]
operator nor increase the scope of the AD.
Cost Impact
The FAA estimates that 33 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 inspections on U.S.
operators is estimated to be $1,386,000, 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 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:
98-16-06 Airbus Industrie: Amendment 39-10682. Docket 96-NM-44-AD.
Applicability: All Model A310 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
A310-53-2030, Revision 5, dated March 6, 1991; at the applicable
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 aft
passenger/crew doors if a steel doubler that covers the entire
inspection area is installed.
(1) For any door on which Modification 5382 has been
accomplished: Perform the initial inspection within 9 years since
airplane manufacture, or within 1 year after the effective date of
this AD, whichever occurs later.
(2) For any door on which Modification 5382 has not been
accomplished, and on which the procedures described in Airbus
Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985, or
Airbus Service Information Letter 53-033, Revision 2, dated November
23, 1984, have been accomplished: Perform the initial inspection
within 5 years since airplane manufacture, or within 1 year after
the effective date of this AD, whichever occurs later.
(3) For any door on which Modification 5382 has not been
accomplished, and on which the procedures described in Airbus
Service Bulletin A310-53-2004, Revision 2, dated June 17, 1985, or
Airbus Service Information Letter 53-033, Revision 2, dated November
23, 1984, have not been accomplished: Perform the initial inspection
within 4 years since airplane 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
A310-53-2041, Revision 02, dated July 2, 1996; at the applicable
times specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD.
Accomplishment of these inspections is not required for the aft
passenger/crew doors if a steel doubler that covers the entire
inspection area is installed.
(1) For the forward 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, on
all Model A310-200 and -300 series airplanes: 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 door on
all Model A310-200 series airplanes: Perform the first inspection
within 5 years or 12,000 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 12,000 landings, whichever occurs first.
(3) For the upper and lower edges of the fail-safe ring and the
upper edges of the corner doubler of the aft passenger/crew door on
all Model A310-300 series airplanes: Perform the first inspection
within 5 years or 7,000 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 7,000 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 A310-53-2041, Revision 02,
dated July 2, 1996. Thereafter, perform the repetitive inspections
required by paragraph (b) of this AD at the applicable times
specified in paragraphs (b)(1), (b)(2), and (b)(3) 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 A310-53-2041, Revision 02,
dated July 2, 1996. Thereafter, perform the repetitive
[[Page 40821]]
inspections required by paragraph (b) of this AD at the applicable
time specified in paragraph (d)(1) or (d)(2) of this AD.
(1) For Model A310-200 series airplanes: Inspect at intervals
not to exceed 5 years or 9,600 landings, whichever occurs first.
(2) For Model A310-300 series airplanes: Inspect at intervals
not to exceed 5 years or 5,600 landings, whichever occurs first.
Note 2: Accomplishment of the actions required by paragraph (b),
(c), or (d) of this AD in accordance with Airbus Service Bulletin
A310-53-2041, Revision 1, dated March 6, 1991, prior to the
effective date of this AD, is acceptable for compliance with that
paragraph.
(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 A310-53-2037,
Revision 1, dated April 29, 1992, and at the applicable times
specified in paragraphs (e)(1), (e)(2), and (e)(3) 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 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 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 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 A310-53-2037,
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 A310-53-2037,
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 A310-53-2017, Revision 7, dated
February 25, 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 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.
(j) Special flight permits may be issued in accordance with
Secs. 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 paragraphs (g)(2) and (h), the actions
shall be done in accordance with the following Airbus service
bulletins, which contain the specified 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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A310-53-2030, Revision 5, March 1-2, 4-5, 7-9, 14. 5............................ March 6, 1991.
6, 1991.
3, 6, 10-13,15-17. 4............................ December 5, 1990.
A310-53-2041, Revision 02, July 1-21.............. 02........................... July 2, 1996.
2, 1996.
A300-53-2037, Revision 1, April 1, 4, 6, 11-15, 1............................ April 29, 1992.
29, 1992. 18, 29, 39-44,
46, 57.
2-3, 5, 7-10, 16- Original..................... December 11, 1990.
17, 19-28, 30-38,
45, 47-56, 58-60.
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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 4: 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.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-20338 Filed 7-30-98; 8:45 am]
BILLING CODE 4910-13-U
