[Federal Register Volume 62, Number 183 (Monday, September 22, 1997)]
[Rules and Regulations]
[Pages 49430-49431]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 97-25055]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-07-AD; Amendment 39-10140; AD 97-20-02]
RIN 2120-AA64
Airworthiness Directives; Lockheed Model L-188A and L-188C Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to all Lockheed Model L-188A and L-188C series airplanes.
This amendment requires revising the Airplane Flight Manual (AFM) to
prohibit the positioning of the power levers below the flight idle stop
during flight, and to provide a statement of the consequences of
positioning the power levers below flight idle stop. This amendment is
prompted by incidents and accidents involving airplanes equipped with
turboprop engines where the propeller ground beta was used improperly
during flight. The actions specified by this AD are intended to prevent
loss of airplane controllability, or engine overspeed and consequent
loss of engine power caused by the power levers being positioned below
the flight idle stop while the airplane is in flight.
DATES: Effective October 27, 1997.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 27, 1997.
ADDRESSES: The service information referenced in this AD may be
obtained from Lockheed Aeronautical Systems Support Company (LASSC),
Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive,
Smyrna, Georgia. 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 FAA, Small
Airplane Directorate, Atlanta Aircraft Certification Office, 1895
Phoenix Boulevard, Suite 450, Atlanta, Georgia; or at the Office of the
Federal Register, 800 North Capitol Street, NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Thomas Peters, Aerospace Engineer,
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane
Directorate, Atlanta Aircraft Certification Office, 1895 Phoenix
Boulevard, Suite 450, Atlanta,-Georgia 30349; telephone (770) 703-7367;
fax (770) 703-7348.
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 Lockheed Model L-188A and L-
188C series airplanes was published in the Federal Register on April
22, 1997 (62 FR 19526). That action proposed to require revising the
Limitations Section of the Airplane Flight Manual (AFM) to prohibit the
positioning of the power levers below the flight idle stop during
flight, and to provide a statement of the consequences of positioning
the power levers below flight idle stop.
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, but remarks that, if an
inherent design problem exists on the affected airplanes to allow
flightcrews to select the power levers below the flight idle stop while
in flight, the FAA should consider the addition of a mechanical means
to preclude such selection. The FAA acknowledges the commenter's
concern, and may consider additional rulemaking to address that concern
in the future on certain airplanes. However, until such final action is
identified, the FAA considers it appropriate to proceed with issuance
of this final rule. No change to the final rule is required.
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 as proposed.
Cost Impact
There are approximately 75 Lockheed Model L-188A and L-188C series
airplanes of the affected design in the worldwide fleet. The FAA
estimates that 32 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
[[Page 49431]]
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
$1,920, or $60 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the proposed 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.
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:
97-20-02 Lockheed: Amendment 39-10140. Docket 97-NM-07-AD.
Applicability: All Model L-188A and L-188C 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 loss of airplane controllability or engine overspeed
with consequent loss of engine power caused by the power levers
being positioned below the flight idle stop while the airplane is in
flight, accomplish the following:
(a) Within 30 days after the effective date of this AD, revise
the Limitations Section of the FAA-approved Airplane Flight Manual
(AFM) to include the following statements. This action may be
accomplished by inserting either a copy of this AD into the AFM or
the revision to the Limitations Section of the FAA-approved Electra
188A or 188C AFM, both dated October 17, 1996, as applicable.
Positioning of power levers below the flight idle stop while the
airplane is in flight is prohibited. Such positioning may lead to
loss of airplane control or may result in an overspeed condition and
consequent loss of engine power.
(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, Atlanta Aircraft Certification
Office (ACO), FAA, Small Airplane Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Operations Inspector, who may add comments and then send it to the
Manager, Atlanta ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Atlanta ACO.
(c) 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.
(d) The AFM revision shall be done in accordance with Electra
188A Airplane Flight Manual, dated October 17, 1996; or Electra 188C
Airplane Flight Manual, dated October 17, 1996; as applicable. 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 Lockheed Aeronautical Systems
Support Company (LASSC), Field Support Department, Dept. 693, Zone
0755, 2251 Lake Park Drive, Smyrna, Georgia. Copies may be inspected
at the Federal Aviation Administration (FAA), Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
FAA, Small Airplane Directorate, Atlanta Aircraft Certification
Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College
Park, Georgia; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
(e) This amendment becomes effective on October 27, 1997.
Issued in Renton, Washington, on September 16, 1997.
James V. Devany,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 97-25055 Filed 9-19-97; 8:45 am]
BILLING CODE 4910-13-U
