[Federal Register Volume 63, Number 55 (Monday, March 23, 1998)]
[Rules and Regulations]
[Pages 13776-13778]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-7365]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-NM-212-AD; Amendment 39-10419; AD 98-07-01]
RIN 2120-AA64


Airworthiness Directives; British Aerospace BAe Model ATP 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain British Aerospace BAe Model ATP airplanes, that 
requires inspections and tests for damage of the engine power cables, 
and replacement of any damaged cable with a new cable. This amendment 
also provides for optional modification of the engine power control 
cable pulley assembly. This amendment is prompted by a report of 
failure of an engine power cable, which could cause loss of function of 
the power control levers on the console. The actions specified by this 
AD are intended to prevent loss of function of the power control levers 
on the console, and subsequent loss of normal control of engine power.

DATES: Effective April 27, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director

[[Page 13777]]

of the Federal Register as of April 27, 1998.

ADDRESSES: The service information referenced in this AD may be 
obtained from AI(R) American Support, Inc., 13850 Mclearen Road, 
Herndon, Virginia 20171. 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 certain British Aerospace BAe 
Model ATP airplanes was published in the Federal Register on September 
13, 1995 (60 FR 47501). That action proposed to require inspections and 
tests for damage of the engine power cables, and replacement of any 
damaged cable with a new cable.

Comments

    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.

Actions Since Issuance of Proposal

    Since the issuance of the proposal, the manufacturer has issued 
British Aerospace Service Bulletin ATP-76-18, dated June 21, 1995, 
which describes procedures for the modification of the engine power 
control cable pulley assembly. The modification involves increasing the 
diameter of the pulley of the engine power control quadrant's lower 
pulley group between stations 398FS to 408FS from 1.5 inches to 2.36 
inches, and repositioning of the lower pulley group slightly forward 
and upward. The service bulletin specifies that, if accomplished, this 
modification would extend the fatigue life of the engine power control 
cables, and would allow the repetitive inspection interval to be 
increased from 1,000 landings to 5,000 landings. The Civil Aviation 
Authority (CAA), which is the airworthiness authority for the United 
Kingdom, classified this service bulletin as optional.
    The FAA has revised this final rule to add accomplishment of this 
modification as an option to permit extension of the repetitive 
inspection interval specified in this AD. Additionally, the cost impact 
information, below, has been revised to specify the number of work 
hours that would be required to accomplish the optional modification.

Conclusion

    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 with the change previously 
described. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    The FAA estimates that 10 airplanes of U.S. registry will be 
affected by this AD, that it will take approximately 2 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 $1,200, or $120 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.
    Should an operator elect to accomplish the optional modification 
provided by this AD, it would take approximately 80 work hours per 
airplane to accomplish it, at an average labor rate of $60 per work 
hour. Based on these figures, the cost impact of this optional 
modification is estimated to be $4,800 per airplane.

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.

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:

98-07-01  British Aerospace Regional Aircraft [Formerly Jetstream 
Aircraft Limited, British Aerospace (Commercial Aircraft) Limited]: 
Amendment 39-10419. Docket 94-NM-212-AD.

    Applicability: BAe Model ATP airplanes, constructor's numbers 
2002 through 2063 inclusive; 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 prevent loss of function of the power control levers on the 
console, and subsequent loss of normal control of engine power due 
to failure of the engine power cables, accomplish the following:
    (a) Perform a detailed visual inspection and tests for damage of 
the engine power cables, in accordance with Jetstream Service 
Bulletin ATP-76-16, dated October 14, 1994,

[[Page 13778]]

at the earlier of the times specified in paragraphs (a)(1) and 
(a)(2) of this AD. Thereafter repeat this inspection and tests at 
intervals not to exceed 1,000 landings.
    (1) Prior to the accumulation of 1,000 total landings on the 
engine power cable, or within 200 landings after the effective date 
of this AD, whichever occurs later.
    (2) Within 75 days after the effective date of this AD.
    (b) If any damaged engine power cable is found, prior to further 
flight, replace the damaged engine power cable with a new cable in 
accordance with Jetstream Service Bulletin ATP-76-16, dated October 
14, 1994. Except as provided by paragraph (c) of this AD, repeat the 
inspection and tests required by paragraph (a) of this AD thereafter 
at intervals not to exceed 1,000 landings.
    (c) Modification of the engine power control cable pulley 
assembly in accordance with British Aerospace Service Bulletin ATP-
76-18, dated June 21, 1995, allows the interval for accomplishment 
of the repetitive inspection and tests required by paragraph (a) of 
this AD to be increased to 5,000 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, International Branch, ANM-116, 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, 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.

    (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 inspection, tests, and replacement shall be done in 
accordance with Jetstream Service Bulletin ATP-76-16, dated October 
14, 1994. The modification, if accomplished, shall be done in 
accordance with Jetstream Service Bulletin ATP-76-18, dated June 21, 
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 AI(R) American Support, Inc., 
13850 Mclearen Road, Herndon, Virginia 20171. 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 April 27, 1998.

    Issued in Renton, Washington, on March 16, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-7365 Filed 3-20-98; 8:45 am]
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