[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]



-----------------------------------------------------------------------


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.

-----------------------------------------------------------------------

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