AD Amdt-39-10015

[Federal Register Volume 62, Number 87 (Tuesday, May 6, 1997)]
[Rules and Regulations]
[Pages 24567-24568]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 97-11522]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-188-AD; Amendment 39-10015; AD 97-10-03]
RIN 2120-AA64


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 repetitive ultrasonic inspections to detect 
cracking of the lugs of the engine mounting beams, and replacement of 
the beam with a serviceable part, if necessary. This amendment is 
prompted by reports of fatigue cracking of the lugs of the engine 
mounting beams. The actions specified by this AD are intended to detect 
and correct such cracking of the engine mounting lugs, which could 
result in reduced structural capability of the engine mount.

DATES: Effective June 10, 1997.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 10, 1997.

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: Tim Backman, Aerospace Engineer, 
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206) 
227-2797; 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 February 14, 1997 (62 FR 6892). That action proposed to require 
repetitive ultrasonic inspections to detect cracking of the lugs of the 
lower forward, lower rear, upper forward, and upper rear engine 
mounting beams, and replacement of the beam with a serviceable part, if 
necessary.
    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 31 British Aerospace Model BAC 1-11 200 and 
400 series airplanes of U.S. registry will be affected by this AD, that 
it will take approximately 6 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 cost impact of the AD on U.S. operators is 
estimated to be $11,160, or $360 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.

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.

[[Page 24568]]

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:

97-10-03  British Aerospace Airbus Limited (Formerly British 
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft 
Group): Amendment 39-10015. Docket 96-NM-188-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 request approval for an 
alternative method of compliance in accordance with paragraph (d) 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 cracking of the engine mounting lugs, 
which could result in reduced structural capability of the engine 
mount; accomplish the following:
    (a) Perform an ultrasonic inspection to detect cracking of the 
lugs of the lower forward, lower rear, upper forward, and upper rear 
of the engine mounting beams in accordance with British Aerospace 
Alert Service Bulletin 53-A-PM6032, Issue No. 1, dated April 7, 
1995, and at the earliest of the times specified in paragraph 
(a)(1), (a)(2), or (a)(3) of this AD.
    (1) Within 850 landings after the effective date of this AD. Or
    (2) Within 1,700 flight hours after the effective date of this 
AD. Or
    (3) Within 2 years after the effective date of this AD.
    (b) If no cracking is detected, repeat the inspection thereafter 
at intervals not to exceed 1,700 flight hours or 850 landings, 
whichever occurs first.
    (c) If any cracking is detected, prior to further flight, 
replace the engine mounting beam in accordance with British 
Aerospace Alert Service Bulletin 53-A-PM6032, Issue No. 1, dated 
April 7, 1995.
    (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 and replacement shall be done in accordance 
with British Aerospace Alert Service Bulletin 53-A-PM6032, Issue No. 
1, dated April 7, 1995. 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 June 10, 1997.

    Issued in Renton, Washington, on April 28, 1997.
Neil D. Schalekamp,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 97-11522 Filed 5-5-97; 8:45 am]
BILLING CODE 4910-13-U