[Federal Register Volume 63, Number 82 (Wednesday, April 29, 1998)]
[Rules and Regulations]
[Pages 23382-23385]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-11088]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-59-AD; Amendment 39-10504; AD 98-09-23]
RIN 2120-AA64


Airworthiness Directives; Lockheed Model L-1011 Series Airplanes 
Equipped With Rolls Royce Model RB211-22B Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), applicable to certain Lockheed Model L-1011 series airplanes, 
that currently requires various modifications and corrective actions to 
prevent a potential fire hazard caused by heat damage to the flex fuel 
feed line from an undetected gearbox fire. In lieu of the various 
modifications and corrective actions, that AD also provides for an 
optional terminating action (i.e., installation of a vent air tube in 
the gear compartment and thickened gearbox housings) for another 
existing AD. For airplanes on which that optional terminating action 
has been accomplished, this amendment requires accomplishment of the 
various modifications and corrective actions. This amendment is 
prompted by a report indicating that, due to bearing failure, an in-
flight fire occurred on an airplane on which a thickened gearbox 
housing was installed. The actions specified by this AD are intended to 
detect and correct bearing failure, which could lead to a fire in the 
gearbox.

DATES: Effective June 3, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of June 3, 1998.


[[Page 23383]]


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 30080. 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, One Crown 
Center, 1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Thomas B. Peters, Aerospace Engineer, 
Systems and Flight Test Branch, ACE-116A, FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown Center, 
1895 Phoenix Boulevard, suite 450, Atlanta, Georgia 30349; telephone 
(770) 703-6063; fax (770) 703-6097.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 87-07-10, 
amendment 39-5597 (52 FR 10736, April 3, 1987), which is applicable to 
certain Lockheed Model L-1011 series airplanes, equipped with Rolls 
Royce Model RB211-22B engines, was published in the Federal Register on 
July 18, 1997 (62 FR 38491). That action proposed to continue to 
require various modifications and corrective actions to prevent a 
potential fire hazard caused by heat damage to the flex fuel feed line 
from an undetected gearbox fire. In lieu of the various modifications 
and corrective actions, that action also provided for an optional 
terminating action (i.e., installation of a vent air tube in the gear 
compartment and thickened gearbox housings) for another existing AD. 
For airplanes on which the optional terminating action has been 
accomplished, that action proposed to require accomplishment of the 
various modifications and corrective actions.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter supports the proposed rule.
    The Air Transport Association (ATA) of America, on behalf of one of 
its members, requests that any alternative method of compliance 
approved previously for compliance with paragraphs (a) and (b) of AD 
87-07-10 be approved as an alternative method of compliance for this 
proposed AD. The FAA concurs with the commenter's request. Paragraph 
(e) of this final rule has been revised to indicate that any approval 
of an alternative method of compliance that was granted previously for 
AD 87-07-10 is approved as an alternative method of compliance with the 
requirements of paragraphs (a) and (b) of this AD.
    The ATA, on behalf of another commenter, states that the proposed 
AD is unnecessary. The commenter notes that the proposal is somewhat 
redundant in that it only eliminates an alternative method of 
compliance with AD 87-07-10. The commenter further states that neither 
AD 87-07-10 nor the proposed AD does anything to address the basic 
problem, which is failure of accessory gearbox bearings. According to 
the commenter, several enhancements have been made over the years to 
prevent bearing failures, which, if unnoticed by available monitoring 
methods (chip detectors), could result in fires. The commenter believes 
that proper management of the chip detector monitoring and improvements 
available to upgrade the accessory gearbox bearings make the proposed 
AD and contemplated breather temperature sensors unnecessary. Last, the 
commenter notes that the latest gearbox fires did not occur in an 
RB211-22B-style gearbox.
    The FAA does not concur that issuance of this AD is unnecessary. 
The commenter is correct in noting that the latest gearbox fires did 
not occur in an RB211-22B-style gearbox. Rather, fires have occurred in 
engines with the thicker, RB211-524-style gearbox housings. In light of 
this more recent service experience, it is evident that the 
installation of the thicker gearbox housings is not, in itself, 
sufficient to eliminate the unsafe condition addressed in AD 87-07-10. 
Therefore, AD 87-07-10 is being superseded to eliminate the 
installation of those gearbox housings, without further action, as an 
approved method of compliance.
    The commenter is also correct in noting that the basic problem is 
failure of accessory gearbox bearings. There are, however, no known 
means to completely eliminate the possibility that such bearings could 
fail and precipitate fires. It is, therefore, necessary to ensure that 
any fire that does occur in the gearbox housing can be detected in a 
timely manner. Compliance with the requirements of this AD will ensure 
that, in the event such a fire does occur, the flight crew can take 
corrective action, i.e., engine shutdown and discharge of the fire 
suppression system, on a timely basis.

Conclusion

    After careful review of the available data, including the comments 
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

    There are approximately 130 Lockheed Model L-1011 series airplanes 
equipped with Rolls Royce Model RB211-22B engines of the affected 
design in the worldwide fleet. The FAA estimates that 76 airplanes of 
U.S. registry will be affected by this AD.
    The actions that are currently required by AD 87-07-10 take 
approximately 3 work hours per engine (3 engines per airplane) to 
accomplish, at an average labor rate of $60 per work hour. Required 
parts for Walter Kidde systems will cost approximately $2,100 per 
engine. Required parts for Graviner systems will cost approximately 
$8,100 per engine. Based on these figures, the cost impact of the 
installation currently required by AD 87-07-10 on U.S. operators is 
estimated to be $6,840 per airplane (for Walter Kidde systems) or 
$24,840 per airplane (for Graviner systems).
    The required modification will take approximately 6 work hours per 
airplane to accomplish, at an average labor rate of $60 per work hour. 
Required parts will cost approximately $10,000 per airplane. Based on 
these figures, the cost impact on U.S. operators of the modification 
required by this AD is estimated to be $787,360, or $10,360 per 
airplane.
    The introduction of a vent air tube will take approximately 3 work 
hours per engine (3 engines per airplane) to accomplish, at an average 
labor rate of $60 per work hour. Required parts will cost approximately 
$500 per engine. Based on these figures, the cost impact on U.S. 
operators of the introduction of a vent air tube required by this AD is 
estimated to be $155,040, or $2,040 per airplane.
    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the current or proposed 
requirements of this AD action, and that no operator would accomplish 
those actions in the future if this AD were not adopted.

[[Page 23384]]

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 removing amendment 39-5597 (52 FR 
10736, April 3, 1987), and by adding a new airworthiness directive 
(AD), amendment 39-10504, to read as follows:

98-09-23  Lockheed: Amendment 39-10504. Docket 96-NM-59-AD. 
Supersedes AD 87-07-10, Amendment 39-5597.

    Applicability: Model L-1011 series airplanes equipped with Rolls 
Royce RB211-22B engines, certificated in any category.

    Note 1: If an operator has accomplished the requirements of 
paragraphs (a) and (b) of this AD on any affected airplane and, 
subsequently, installs a different Model RB211-22B engine on that 
airplane, the airplane and all installed engines are still subject 
to the requirements of this AD.

    Note 2: 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 (e) 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 bearing failure, which could lead to a 
fire in the gearbox, accomplish the following:
    (a) Within 8,000 flight hours or 30 months after May 8, 1987 
(the effective date of AD 87-07-10, amendment 39-5597), whichever 
occurs first, accomplish the procedures specified in the 
Accomplishment Instructions of the service bulletins listed in 
paragraphs (a)(1) and (a)(2) of this AD.
    (1) Lockheed Service Bulletin 093-26-036, dated April 1, 1986, 
Installation of Fire Detector Segment; and
    (2) Lockheed Service Bulletin 093-71-067, Revision 1, dated 
April 1, 1986, Gearbox Breather Duct Modification.
    (b) Within 8,000 flight hours or 30 months after May 8, 1987, 
whichever occurs first, accomplish the procedures specified in the 
Accomplishment Instructions of the service bulletins listed in 
paragraphs (b)(1) and (b)(2) of this AD.
    (1) Rolls Royce Service Bulletin RB.211-72-4666, Revision 3, 
dated October 14, 1977, Introduction of Vent Air Tube in Gear 
Compartment; and
    (2) Rolls Royce Service Bulletin RB.211-72-8138, dated March 21, 
1986, Installation of Additional No. 7 Fire Sensor.
    (c) For airplanes on which Rolls Royce Service Bulletin RB.211-
72-4666, Revision 3, dated October 14, 1977, and Rolls Royce Service 
Bulletin RB.211-72-3878, Revision 3, dated June 25, 1976, have been 
accomplished in accordance with paragraph C. of AD 87-07-10: Within 
48 months or 16,000 flight hours after the effective date of this 
AD, whichever occurs first, accomplish the actions specified in 
paragraphs (a) and (b) of this AD.
    (d) Accomplishment of the requirements of paragraphs (a) and (b) 
of this AD; or accomplishment of the requirements of paragraph (c) 
of this AD; constitutes terminating action for the requirements of 
AD 85-09-03, amendment 39-5056. The AFM limitations required by AD 
85-09-03 may be removed following accomplishment of the terminating 
action.
    (e)(1) 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 
Maintenance Inspector, who may add comments and then send it to the 
Manager, Atlanta ACO.
    (2) Alternative methods of compliance, approved previously in 
accordance with AD 87-07-10, amendment 39-5597, are approved as 
alternative methods of compliance with paragraphs (a) and (b) of 
this AD.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Atlanta ACO.

    (f) Special flight permits may be issued in accordance with 
Secs. 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.
    (g) The actions shall be done in accordance with the following 
service bulletins, which contain the specified effective pages:

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                                                                   Revision level shown                         
Service bulletin referenced and date            Page No.                  on page           Date shown on page  
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Lockheed Service Bulletin 093-26-     1-7........................  Original............  April 1, 1986.         
 036, April 1, 1986.                                                                                            
Lockheed Service Bulletin 093-71-     1-7, 9-11..................  1...................  April 1, 1986.         
 067, Revision 1, April 1, 1986.                                                                                
                                      8..........................  Original............  February 5, 1986.      
Rolls Royce Service Bulletin RB.211-  1-34.......................  Original............  March 21, 1986.        
 72-8138, March 21, 1986.                                                                                       

[[Page 23385]]

                                                                                                                
Rolls Royce Service Bulletin RB.211-  1..........................  3...................  October 14, 1977.      
 72-4666, Revision 3, October 14,                                                                               
 1977.                                                                                                          
                                      2-6, 6A, 7-10..............  2...................  August 26, 1977.       
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    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 30080. Copies may be 
inspected at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the FAA, Small Airplane 
Directorate, Atlanta Aircraft Certification Office, One Crown 
Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW., suite 700, Washington, DC.
    (h) This amendment becomes effective on June 3, 1998.

    Issued in Renton, Washington, on April 21, 1998.
Gary L. Killion,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-11088 Filed 4-28-98; 8:45 am]
BILLING CODE 4910-13-U