AD Amdt-39-11157

[Federal Register Volume 64, Number 86 (Wednesday, May 5, 1999)]
[Rules and Regulations]
[Pages 24034-24035]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 99-11223]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-307-AD; Amendment 39-11157; AD 99-10-03]
RIN 2120-AA64


Airworthiness Directives; British Aerospace Model BAC 1-11 200 
and 400 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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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 an inspection to detect cracking of the flap 
control lever and to identify the material from which the lever is 
made; replacement of the flap control lever with an improved part, if 
necessary; and repetitive inspections for airplanes having a lever made 
from certain material. This amendment is prompted by issuance of 
mandatory continuing airworthiness information by a foreign civil 
airworthiness authority. The actions specified by this AD are intended 
to prevent failure of the flap control lever, which could result in 
restricted flap movement and consequent reduced controllability of the 
airplane.

DATES: Effective June 9, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 9, 1999.

ADDRESSES: The service information referenced in this AD may be 
obtained from British Aerospace, Service Support, 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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; 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 British Aerospace Model BAC 1-
11 200 and 400 series airplanes was published in the Federal Register 
on February 18, 1999 (64 FR 8027). That action proposed to require an 
inspection to detect cracking of the flap control lever and to identify 
the material from which the lever is made; replacement of the flap 
control lever with an improved part, if necessary; and repetitive 
inspections for airplanes having a lever made from certain material.

Comments

    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 42 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 1 work hour 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 $2,520, or $60 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 24035]]

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:

99-10-03  British Aerospace Airbus Limited (Formerly British 
Aerospace Commercial Aircraft Limited, British Aerospace Aircraft 
Group): Amendment 39-11157. Docket 98-NM-307-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 (b) 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 prevent failure of the flap control lever, which could result 
in restricted flap movement and consequent reduced controllability 
of the airplane, accomplish the following:
    (a) Within 12 months after the effective date of this AD, 
perform a one-time detailed visual inspection of the flap control 
lever to detect cracking, and to identify the type of aluminum alloy 
from which the flap control lever is made, in accordance with 
British Aerospace Alert Service Bulletin 27-A-PM6041, Issue 1, dated 
August 21, 1998.
    (1) If no crack is detected and the lever is made of L97 or L99 
aluminum alloy, no further action is required by this AD.
    (2) If no crack is detected, and the lever is made of L53 
aluminum alloy or the material of the flap control lever cannot be 
identified, repeat the inspection thereafter at intervals not to 
exceed 24 months; or prior to further flight, replace the flap 
control lever with a flap control lever made of L97 or L99 aluminum 
alloy, in accordance with the alert service bulletin. Following such 
replacement, no further action is required by this AD.
    (3) If any crack is detected, prior to further flight, replace 
the flap control lever with a flap control lever made of L97 or L99 
aluminum alloy, in accordance with the alert service bulletin. After 
the replacement, no further action is required by this AD.

Alternative Methods of Compliance

    (b) 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, International Branch, ANM-116. 
Operators shall submit their requests through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, International Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

Special Flight Permits

    ( c) Special flight permits may be issued in accordance with 
Sec. 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.

Incorporation by Reference

    (d) The inspections and replacement shall be done in accordance 
with British Aerospace Alert Service Bulletin 27-A-PM6041, Issue 1, 
dated August 21, 1998. 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, Service Support, 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.

    Note 3: The subject of this AD is addressed in British 
airworthiness directive 003-08-98.

    (e) This amendment becomes effective on June 9, 1999.

    Issued in Renton, Washington, on April 28, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-11223 Filed 5-4-99; 8:45 am]
BILLING CODE 4910-13-P