[Federal Register Volume 61, Number 83 (Monday, April 29, 1996)]
[Proposed Rules]
[Pages 18700-18704]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10508]
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DEPARTMENT OF AGRICULTURE
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-109-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and B4 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
[[Page 18701]]
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the supersedure of an existing
airworthiness directive (AD), applicable to certain Airbus Model A300
B2 and B4 series airplanes, that currently requires inspection for
cracks of the fuselage, wings, and vertical stabilizer structures; and
repairs or modifications, if necessary. That AD was prompted by reports
of cracking in several areas of the fuselage, wings, and vertical
stabilizer structure due to fatigue-related stress. The actions
specified by that AD are intended to prevent such fatigue-related
cracking, which could result in reduced structural integrity of the
fuselage, wing, and vertical stabilizer. This action would provide for
a new optional terminating action, for certain airplanes, and would
expand the applicability of the existing AD to include additional
airplanes.
DATES: Comments must be received by June 10, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-109-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, 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: Phil Forde, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206)
227-2146; 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 95-NM-109-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. 95-NM-109-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
On August 13, 1986, the FAA issued AD 86-19-02, amendment 39-5396
(51 FR 29910, August 21, 1986), applicable to certain Airbus Model A300
B2 and B4 series airplanes. That AD requires inspections for cracks of
the fuselage, wings, and vertical stabilizer structures; and repairs or
modifications, if necessary. That action was prompted by reports that,
during fatigue tests conducted by the manufacturer, cracks were
detected in several areas of the fuselage, wings, and vertical
stabilizer structure. The requirements of that AD are intended to
prevent reduced structural integrity of the fuselage, wing, and
vertical stabilizer.
Explanation of New Relevant Service Information
Since the issuance of that AD, Airbus has issued Revision 3 of
Service Bulletin A300-53-182, dated March 16, 1994. The inspection
procedures described in this revision are identical to those described
in the original version of the service bulletin, which was referenced
in AD 86-19-02 as the appropriate source of service information.
However, this new revision of the service bulletin differs in two ways
from the original version:
1. The effectivity listing in the revised bulletin includes
additional airplanes that are subject to the addressed unsafe
condition.
2. For certain airplanes, the revised service bulletin provides
procedures for replacement of the web plate and support fitting at the
level of stringer 18 (left- and right-hand) with a new web plate and
support fitting. Accomplishment of the replacement would eliminate the
need for the repetitive inspections in the web plate between frame 30A
and frame 32 at stringer 18.
The Direction Generale de l'Aviation Civile (DGAC), which is the
airworthiness authority for France, classified this service bulletin as
mandatory and issued French airworthiness directive (CN) 83-102-
053(B)R2, dated March 2, 1994, in order to assure the continued
airworthiness of these airplanes in France.
Explanation of the Provisions of the Proposed Rule
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
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.
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 supersede AD 86-19-02 to
continue to require inspections for cracks of the fuselage, wings, and
vertical stabilizer structures; and repairs or modifications, if
necessary. However, the applicability of the rule would be expanded to
include additional airplanes that have been identified as subject to
the addressed unsafe condition.
For certain airplanes, the proposed AD would provide for a new
optional replacement action, which would constitute terminating action
for certain repetitive inspection requirements. These actions would be
required to be accomplished in accordance with the service bulletin
described previously.
Operators who previously elected to accomplish Airbus Modification
1691 to terminate the repetitive inspections at stringers 18 and 22, as
was provided by paragraph D. of AD 86-19-02, should note that, under
the provisions of paragraph (d)(4) of this proposal, accomplishment of
that modification
[[Page 18702]]
would constitute terminating action for the repetitive inspections only
at stringer 22.
Additionally, operators should note that paragraph G. of AD 86-19-
02 has not been retained in this proposal. That paragraph required
ultrasonic inspections of the longitudinal lap joints at stringer 29
between frames 72 and 73, and eddy current inspections of the
longitudinal skin splices of the top fuselage joint between frames 72
and 80. The FAA has issued a separate rulemaking action to address
those requirements (reference notice of proposed rulemaking, Docket No.
94-NM-246-AD).
Cost Impact
Approximately 7 Airbus Model A300 B2 and B4 series airplanes of
U.S. registry would be affected by this proposed AD.
The actions that are currently required by AD 86-19-02 take
approximately 919 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. The cost of required parts will be
nominal. Based on these figures, the cost impact on U.S. operators of
the actions currently required is estimated to be $385,980, or $55,140
per airplane, per inspection cycle.
The new actions that are proposed in this AD action would take
approximately 3 work hours per airplane to accomplish, at an average
labor rate of $60 per work hour. Based on these figures, the cost
impact on U.S. operators of the proposed requirements of this AD is
estimated to be $1,260, or $180 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the current or 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 removing amendment 39-5396 (51 FR
29910, August 21, 1986), and by adding a new airworthiness directive
(AD), to read as follows:
Airbus Industrie: Docket 95-NM-109-AD. Supersedes AD 86-19-02,
Amendment 39-5396.
-Applicability: All Model A300 B2 and B4 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 (j) 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.
Note 2: Airbus Model A300-600 series airplanes are not subject
to this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fatigue-related cracking, which could result in
reduced structural integrity of the fuselage, wing, and vertical
stabilizer, accomplish the following:
(a) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-127, Revision 4, dated May 10, 1984: Perform a
visual inspection to detect cracks in the upper fuselage skin at
frame 58 between stringer 5 left and stringer 5 right, in accordance
with the Accomplishment Instructions of the service bulletin, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (a)(1)(i) or (a)(1)(ii) of this AD.
(i) Prior to the accumulation of 18,000 total landings or 18,000
total flight hours, whichever occurs earlier; or
(ii) Within one year after September 26, 1986 (the effective
date of AD 86-19-02, amendment 39-5396).
(2) If no crack is detected, repeat this inspection thereafter
at intervals not to exceed 3,000 flight hours.
(3) If any crack is detected, prior to further flight, repair it
in accordance with Figure 2, ``Inspection and Repair Alternative
Chart,'' of the service bulletin.
(4) Installation of Airbus Modification 2147 (reference Airbus
Service Bulletin A300-53-110, Revision 10, dated April 7, 1986) or
Airbus Modification 2526/1693 (reference Airbus Service Bulletin
A300-53-128, Revision 5, dated May 10, 1984) constitutes terminating
action for the repetitive inspection requirements of paragraph
(a)(2) of this AD.
(b) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-101, Revision 7, dated May 10, 1984: Perform a
radiographic and ultrasonic inspection to detect cracks in the
circumferential fuselage splice plates and stringer couplings, in
accordance with the Accomplishment Instructions of the service
bulletin, and in accordance with the times specified in this
paragraph.
(1) Perform the initial inspections at the applicable time
specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD:
(i) For airplanes on which the actions specified in Airbus
Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have
been accomplished previously: Inspect prior to the accumulation of
20,000 landings since accomplishment of those actions, or within one
year after September 26, 1986, whichever occurs later.
(ii) For airplanes on which the actions specified in Airbus
Service Bulletin A300-53-053, Revision 2, dated July 30, 1981, have
not been accomplished: Inspect prior to the accumulation of 18,000
total landings, or within one year after September 26, 1986,
whichever occurs later.
(2) If no crack is detected, repeat the inspections thereafter
at intervals not to exceed 3,000 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with Figures 1 and 2 of the service bulletin.
(4) Installation of Airbus Modification 3760 (reference Airbus
Service Bulletin A300-53-170, Revision 1, dated January 25, 1985)
constitutes terminating action for the repetitive inspection
requirements of paragraph (b)(2) of this AD.
(c) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-143, Revision 3, dated May 10, 1984: Perform a
visual inspection to detect cracks in frame
[[Page 18703]]
57A between stringers 15 and 16 (left- and right-hand), and the
stringer 5 connection angle at frame 65 (left- and right-hand), in
accordance with the Accomplishment Instructions of the service
bulletin, and in accordance with the times specified in this
paragraph. .
(1) Perform the initial inspection at the later of the times
specified in paragraph (b)(1)(i) or (b)(1)(ii) of this AD:
(i) Prior to the accumulation of 20,000 total landings; or
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat this inspection thereafter
at intervals not to exceed 3,000 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 2643 (reference Airbus
Service Bulletin A300-53-132, Revision 4, dated May 10, 1984)
constitutes terminating action for the repetitive inspection
requirement of paragraph (c)(2) of this AD.
(d) For airplanes having serial number 002 through 156
inclusive, on which Airbus Modification 2611 has not been installed:
Perform a visual inspection, and liquid penetrant test if
applicable, to detect cracks in the web plate and support fitting
between frames 30A and 32 at stringer 18, and between stringers 22
and 23 (left- and right-hand), in accordance with Airbus Service
Bulletin A300-53-182, Revision 3, dated March 16, 1994, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (d)(1)(i) or (d)(1)(ii) of this AD:
(i) Prior to the accumulation of 30,000 total landings; or
(ii) Within 1,500 landings after the effective date of this AD.
(2) If no crack is detected, repeat the inspection at the
applicable intervals specified in paragraph (d)(2)(i) or (d)(2)(ii)
of this AD.
(i) If, at the time of the most recent inspection, the airplane
has accumulated fewer than 36,000 total landings, repeat the
inspection thereafter at intervals not to exceed 3,000 landings.
(ii) If, at the time of the most recent inspection, the airplane
has accumulated 36,000 or more total landings, repeat the inspection
thereafter at intervals not to exceed 2,000 landings.
(3) If any crack is detected in the web plate between frames 30A
and 32 at stringer 18, prior to further flight, replace the web
plate and support fitting at stringer 18 (left- and right-hand) with
a new web plate and support fitting, in accordance with the service
bulletin. Accomplishment of this replacement constitutes terminating
action for the repetitive inspection requirements for stringer 18 as
required by paragraph (d)(2) of this AD.
(4) If any crack is detected in the web plate between frame 30A
and 32 between stringers 22 and 23, prior to further flight, replace
the web plate and support fitting between stringers 22 and 23 (left-
and right-hand) with a new web plate and support fitting, in
accordance with Airbus Service Bulletin A300-53-182, Revision 3,
dated March 16, 1994. Accomplishment of this replacement constitutes
terminating action for the repetitive inspection requirements for
the subject area between stringers 22 and 23 as required by
paragraph (d)(2) of this AD.
(5) Terminating action for the repetitive inspection
requirements of paragraph (d)(2) of this AD is as follows:
(i) Installation of Airbus Modification 1691 (reference Airbus
Service Bulletin A300-53-063) between stringers 22 and 23
constitutes terminating action for the repetitive inspection
requirements of paragraph (d)(2) of this AD for that area only.
(ii) Replacement of the web plates and support fittings at the
level of stringer 18 (left- and right-hand) with a new web plate and
support fitting, in accordance with Airbus Service Bulletin A300-53-
182, Revision 3, dated March 16, 1994, constitutes terminating
action for the repetitive inspection requirements of paragraph
(d)(2) of this AD for that stringer only.
(iii) Accomplishment of the actions specified in both paragraph
(d)(5)(i) and paragraph (d)(5)(ii) of this AD constitute terminating
action for all repetitive inspection requirements required by
paragraph (d)(2) of this AD.
(e) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-112, Revision 2, dated July 20, 1981: Perform a
visual inspection to detect cracks of the skin from frame 28 to
frame 31 between stringers 29 and 31 (left- and right-hand), in
accordance with the Accomplishment Instructions of the service
bulletin, and in accordance with the times specified in this
paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (e)(1)(i) or (e)(1)(ii) of this AD: -
(i) Prior to the accumulation of 24,000 total landings; or
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat the inspection at the
applicable intervals specified in paragraph (e)(2)(i) or (e)(2)(ii)
of this AD:
(i) If, at the time of the most recent inspection, the airplane
has accumulated fewer than 36,000 total landings, repeat the
inspection thereafter at intervals not to exceed 6,000 landings.
(ii) If, at the time of the most recent inspection, the airplane
has accumulated 36,000 or more total landings, repeat the inspection
thereafter at intervals not to exceed 3,000 landings.
(3) If any crack is found, prior to further flight, install
Airbus Modification 1358 in accordance with Airbus Service Bulletin
A300-53-027, Revision 4, dated January 4, 1984. Accomplishment of
this modification constitutes terminating action for the repetitive
inspection requirements of paragraph (e)(2) of this AD.
(4) Installation of Airbus Modification 1358 (reference Airbus
Service Bulletin A300-53-027, Revision 4, dated January 4, 1984)
constitutes terminating action for the repetitive inspection
requirements of paragraph (e)(2) of this AD.
(f) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-53-100, Revision 1, dated May 10, 1984: Perform an
internal and external visual inspection to detect cracks of the
longitudinal joint at stringer 51 (left- and right-hand) between
frames 72 and 80, in accordance with the Accomplishment Instructions
of the service bulletin, and in accordance with the times specified
in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (f)(1)(i) or (f)(1)(ii) of this AD:
(i) Prior to the accumulation of 12,000 total landings or 15,000
total flight hours, whichever occurs earlier; or
(ii) Within one year after September 26, 1986.
(2) If no crack is found, repeat the internal inspection
thereafter at intervals not to exceed 1,500 flight hours, and repeat
the external inspection thereafter at intervals not to exceed 12,000
flight hours.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 1421 (reference Airbus
Service Bulletin A300-53-033, Revision 3, dated May 10, 1984)
constitutes terminating action for the repetitive inspection
requirements of paragraph (f)(2) of this AD.
(g) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-55-026, Revision 3, dated May 10, 1984: Perform a
visual inspection of the 6 vertical stabilizer attachment fittings
for cracks, which initiate from the rivet holes, in accordance with
the Accomplishment Instructions of the service bulletin, and in
accordance with the times specified in this paragraph.
(1) Perform the initial inspection at the later of the times
specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD:
(i) Prior to the accumulation of 20,000 total landings or 20,000
total flight hours, whichever occurs earlier; or
(ii) Within one year after September 26, 1986, whichever occurs
earlier.
(2) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 1,500 landings.
(3) If any crack is detected, prior to further flight, repair it
in accordance with the service bulletin.
(4) Installation of Airbus Modification 3172 (reference Airbus
Service Bulletin A300-55-024, Revision 4, dated May 25, 1984)
constitutes terminating action for the repetitive inspection
requirements of paragraph (g)(2) of this AD.
(h) For airplanes with serial numbers listed in Airbus Service
Bulletin A300-57-109, Revision 1, dated July 10, 1982: Perform a
visual inspection to detect cracks in the landing angle attached to
the outboard side of the wing leading edge at nose rib 8 (left- and
right-hand), in accordance with the Accomplishment Instructions of
the service bulletin, and in accordance with the times specified in
this paragraph.
(1) Perform the initial inspecton at the later of the times
specified in paragraph (h)(1)(i) or (h)(1)(ii):
(i) Prior to the accumulation of 15,000 total landings; or
[[Page 18704]]
(ii) Within one year after September 26, 1986.
(2) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 3,000 landings.
(3) If any crack is detected, within the next 1,000 landings
following crack detection, install Airbus Modification 1307 in
accordance with Airbus Service Bulletin A300-57-026, Revision 3,
dated October 21, 1982.
(4) Installation of Airbus Modification 1307 (reference Airbus
Service Bulletin A300-57-026, Revision 3, dated October 21, 1982)
constitutes terminating action for the repetitive inspection
requirements of paragraph (h)(2) of this AD.
(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) 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 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
Issued in Renton, Washington, on April 23, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-10508 Filed 4-26-96; 8:45 am]
BILLING CODE 4910-13-P