[Federal Register Volume 60, Number 182 (Wednesday, September 20, 1995)]
[Rules and Regulations]
[Pages 48635-48636]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-22857]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-NM-184-AD; Amendment 39-9374; AD 95-19-12]
Airworthiness Directives; British Aerospace Model BAC 1-11 200
and 400 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 British Aerospace Model BAC 1-11 200 and 400 series
airplanes, that requires various repetitive inspections to detect
cracks in certain panels of the lower skin of the wing, and in certain
fixed ribs of the leading edge of the wing. This amendment also
requires repair or replacement of cracked parts, which would terminate
certain repetitive inspections. This amendment is prompted by reports
of cracking in certain panels of the lower skin of the wing, and in
certain fixed ribs of the leading edge of the wing due to fatigue-
related stress. The actions specified by this AD are intended to ensure
the structural integrity of the wing by detecting fatigue-related
cracking in a timely manner in the panels of the lower skin of the wing
or in the fixed ribs of the leading edge of the wing.
DATES: Effective October 20, 1995.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 20, 1995.
ADDRESSES: The service information referenced in this AD may be
obtained from British Aerospace, Airbus Limited, P.O. Box 77, Bristol
BS99 7AR, England. 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: William Schroeder, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2148; fax (206) 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 British Aerospace Model BAC 1-
11 200 and 400 series airplanes was published in the Federal Register
on June 9, 1995 (60 FR 30474). That action proposed to require various
repetitive inspections to detect cracks in panel number 1 at rib 6 and
in panel number 2 at rib 10 of the lower skin of the wing, in the
rebate radius of panel number 2 at the joint between panels 1 and 2 of
the lower skin of the wing, and in the top and bottom flanges of fixed
ribs 6, 10, and 14 of the leading edge of the wing. That action also
proposed to require repair or replacement of cracked parts, which
constitutes terminating action for certain repetitive inspection
requirements.
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.
The commenter supports the proposed rule.
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 as proposed.
The FAA estimates that 31 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 14 work hours per
airplane to accomplish the required actions, and that the average labor
rate is $60 per work hour. Based on these figures, the total cost
impact of the AD on U.S. operators is estimated to be $26,040, or $840
per airplane.
The total 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.
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.
[[Page 48636]]
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-19-12 British Aerospace Airbus Limited (Formerly British
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft
Group): Amendment 39-9374. Docket 94-NM-184-AD.
Applicability: All Model BAC 1-11 200 and 400 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 use the authority
provided in paragraph (d) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To ensure the structural integrity of the wing, accomplish the
following:
(a) Prior to the accumulation of 12,000 total landings or within
1,500 landings after the effective date of this AD, whichever occurs
later, perform a close visual and dye penetrant inspection to detect
cracks in panel number 1 at rib 6 and in panel number 2 at rib 10 of
the lower skin of the wing, in accordance with British Aerospace
Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.
(1) If no crack is detected, repeat the inspections thereafter
at intervals not to exceed 8,000 landings.
(2) If any crack is detected at rib 6, prior to further flight,
repair panel number 1 in accordance with the alert service bulletin.
Accomplishment of this repair constitutes terminating action for the
repetitive inspections of panel number 1 as required by this
paragraph.
(3) If any crack is detected at rib 10, prior to further flight,
repair panel number 2 in accordance with a method approved by the
Manager, Standardization Branch, ANM-113, FAA, Transport Airplane
Directorate.
(b) Prior to the accumulation of 30,000 total landings or within
1,500 landings after the effective date of this AD, whichever occurs
later, perform an eddy current inspection to detect cracks in the
rebate radius of panel number 2 at the joint between panels 1 and 2
of the lower skin of the wing, in accordance with British Aerospace
Alert Service Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.
(1) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 8,000 landings.
(2) If any crack is detected, prior to further flight, repair
panel number 2 in accordance with the alert service bulletin.
Accomplishment of this repair constitutes terminating action for the
repetitive inspections of panel number 2 as required by this
paragraph.
(c) Prior to the accumulation of 30,000 total landings or within
1,500 landings after the effective date of this AD, whichever occurs
later, perform a close visual inspection to detect cracks in the top
and bottom flanges of fixed ribs 6, 10, and 14 of the leading edge
of the wing, in accordance with British Aerospace Alert Service
Bulletin 57-A-PM5992, Issue 1, dated October 14, 1992.
(1) If no crack is detected, repeat the inspection thereafter at
intervals not to exceed 8,000 landings.
(2) If any crack is detected, prior to further flight, replace
the cracked rib with a new rib, in accordance with the alert service
bulletin. Prior to the accumulation of 30,000 total landings on the
newly installed rib, perform a close visual inspection to detect
cracks on the newly installed rib in accordance with the service
bulletin. Repeat the inspection thereafter at intervals not to
exceed 8,000 landings.
(d) 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.
(e) 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.
(f) The inspections, certain repairs, and replacement shall be
done in accordance with British Aerospace Alert Service Bulletin 57-
A-PM5992, Issue 1, dated October 14, 1992. 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 British Aerospace, Airbus Limited, P.O. Box 77,
Bristol BS99 7AR, England. 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.
(g) This amendment becomes effective on October 20, 1995.
Issued in Renton, Washington, on September 7, 1995.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-22857 Filed 9-19 -95; 8:45 am]
BILLING CODE 4910-13-U
