[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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