[Federal Register Volume 62, Number 100 (Friday, May 23, 1997)]
[Rules and Regulations]
[Pages 28325-28328]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-12859]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 96-NM-43-AD; Amendment 39-10032; AD 97-11-03]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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[[Page 28326]]
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Airbus Model A300 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 will also require
modification of the passenger/crew door frames, which, when
accomplished, terminates 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 June 27, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 27, 1997.
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: Charles Huber, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2589; 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 series
airplanes was published in the Federal Register on January 29, 1997 (62
FR 4213). 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 require modification of the
passenger/crew door frames, which, when accomplished, constitutes
terminating action for certain inspections.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
The FAA estimates that 4 Airbus Model A300 series airplanes of U.S.
registry will be affected by this AD.
It will take approximately 700 work hours per airplane to
accomplish the required inspections, at an average labor rate of $60
per work hour. Based on these figures, the cost impact of the required
inspections on U.S. operators is estimated to be $168,000, or $42,000
per airplane.
The FAA estimates that it will take approximately 330 work hours
per airplane to accomplish the required modification, and that the
average labor rate is $60 per work hour. Required parts will cost
approximately $1,055 per airplane. Based on these figures, the cost
impact of the required 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 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 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:
97-11-03 Airbus: Amendment 39-10032. 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
[[Page 28327]]
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 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 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 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.
[[Page 28328]]
(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 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.
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.
(j) The inspections and repairs 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 Revision level shown
date Page No. on page Date shown on page
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A300-53-204, Revision 6, October 1, 2, 11, 12........ 6.................... October 11, 1993.
11, 1993.
3-5, 7-10, 13-17.... 3.................... September 25, 1990.
6................... 4.................... April 18, 1991.
A300-53-233, Revision 1, April 18, 1, 6................ 1.................... April 18, 1991.
1991.
2-5, 7-17........... Original............. December 5, 1990.
A300-53-227, Revision 1, April 29, 1-4, 6, 7, 11, 12, 1.................... April 29, 1992.
1992. 16-18, 37-50, 57,
58, 62, 64, 67, 68,
91, 92, 97, 98,
110, 116.
5, 8-10, 13-15, 19- Original............. December 3, 1990.
36, 51-56, 59-61,
63, 65, 66, 69-90,
92A-96, 99-109, 111-
115.
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The modification shall be done in accordance with Airbus Service
Bulletin A300-53-192, Revision 7, dated July 13, 1992, which
contains the following list of effective pages:
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Revision
Page No. level shown Date shown on page
on page
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1, 2, 107, 122................ 7 July 13, 1992.
3, 4, 21, 22, 41-54........... 5 April 11, 1991.
5, 59......................... 4 September 25, 1990.
6, 6A, 7, 8, 11-17, 23, 27, 1 July 24, 1989.
29, 30, 55-58, 60-92, 94-106,
108.
9, 10, 18-20, 24-26, 28, 93, 3 February 5, 1990.
31-40, 110-114, 116-121.
109, 115...................... 6 February 25, 1992.
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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.
(k) This amendment becomes effective on June 27, 1997.
Issued in Renton, Washington, on May 12, 1997.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-12859 Filed 5-22-97; 8:45 am]
BILLING CODE 4910-13-U
