[Federal Register Volume 66, Number 94 (Tuesday, May 15, 2001)]
[Proposed Rules]
[Pages 26817-26819]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-12176]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-47-AD]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717 Series 
Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the adoption of a new airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
717 series airplanes. This proposal would require repetitive 
inspections of the rod ends of the spoiler hold-down actuators for 
breakage along the intersection of the thread runout and the outer 
spherical surface of the lug; and replacement of any broken rod end of 
the spoiler hold-down actuators with a new rod end. This proposal also 
would require replacement of the rod ends of the spoiler hold-down 
actuators with new rod ends, and reidentification of the spoiler hold-
down actuators, which would constitute terminating action for the 
repetitive inspections. This action is necessary to prevent failure of 
the rod ends of the spoiler hold-down actuators due to fatigue, which 
could result in loss of the back-up protection of the spoiler float 
hold-down and unavailability of monitoring for an uncommanded spoiler 
movement. This action is intended to address the identified unsafe 
condition.

DATES: Comments must be received by June 29, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2001-NM-47-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2001-NM-47-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.

[[Page 26818]]

    The service information referenced in the proposed rule may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). This information may 
be examined at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft 
Certification Office, 3960 Paramount Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT: Maureen Moreland, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; 
telephone (562) 627-5238; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION:

Comments Invited

    Interested persons are invited to participate in the making of the 
proposed rule by submitting such written data, views, or arguments as 
they may desire. Communications shall identify the Rules Docket number 
and be submitted in triplicate to the address specified above. All 
communications received on or before the closing date for comments, 
specified above, will be considered before taking action on the 
proposed rule. The proposals contained in this action may be changed in 
light of the comments received.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the proposed 
AD is being requested.
     Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the proposed rule. All 
comments submitted will be available, both before and after the closing 
date for comments, in the Rules Docket for examination by interested 
persons. A report summarizing each FAA-public contact concerned with 
the substance of this proposal will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NM-47-AD.'' The postcard will be date stamped and 
returned to the commenter.

Availability of NPRMs

    Any person may obtain a copy of this NPRM by submitting a request 
to the FAA, Transport Airplane Directorate, ANM-114, Attention: Rules 
Docket No. 2001-NM-47-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    The FAA has received reports of failures of the attach lug rod end 
on the spoiler hold-down actuators on McDonnell Douglas Model 717 
series airplanes. These failures initiated along a region at the 
intersection of the thread runout and the outer spherical surface of 
the lug. Investigation revealed that such failures were caused by 
fatigue rupture with multiple failure origins. Failure of the rod ends 
of the spoiler hold-down actuators due to fatigue, if not corrected, 
could result in loss of the back-up protection of the spoiler float 
hold-down and unavailability of monitoring for an uncommanded spoiler 
movement.

Explanation of Relevant Service Information

    The FAA has reviewed and approved Boeing Alert Service Bulletin 
717-27A0010, dated August 15, 2000. This service bulletin describes 
procedures for repetitive general visual inspections of the rod ends of 
the hold-down actuators of the inboard and outboard spoilers for 
breakage along the intersection of the thread runout and the outer 
spherical surface of the lug; and replacement of any broken rod end of 
the spoiler hold-down actuators with a new rod end.
    The FAA also has reviewed and approved Boeing Service Bulletin 717-
27-0013, dated January 30, 2001, and Revision 01, dated February 28, 
2001. The service bulletin describes procedures for replacement of the 
rod ends of the spoiler hold-down actuators with new rod ends, and 
reidentification of the spoiler hold-down actuators, which would 
eliminate the need for the repetitive inspections described above. The 
effectivity listing of Revision 01 of the service bulletin was revised 
from the original version of the service bulletin to include additional 
airplanes that are subject to the identified unsafe condition.

Explanation of Requirements of Proposed Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would require accomplishment of the actions specified in 
the service bulletins described previously. Accomplishment of the 
actions specified in the service bulletins is intended to adequately 
address the identified unsafe condition.

Explanation of Differences Between Service Bulletin and the 
Proposed AD

    Operators should note that, although the effectivity listing of 
Boeing Service Bulletin 717-27A0010 affects airplanes having 
manufacturer's fuselage numbers 5002 through 5082 inclusive, this 
proposed AD does not affect McDonnell Douglas Model 717 series 
airplanes, manufacturer's fuselage numbers 5002, 5003, 5037 and 
subsequent. Those airplanes had improved rod ends installed during 
production that address the identified unsafe condition of this 
proposed AD. Therefore, those airplanes are not subject to the 
requirements of this proposed AD.

Cost Impact

    There are approximately 33 Model 717 series airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 23 
airplanes of U.S. registry would be affected by this proposed AD.
    It would take approximately 1 work hour per airplane to accomplish 
the proposed inspection, at an average labor rate of $60 per work hour. 
Based on these figures, the cost impact of the inspection proposed by 
this AD on U.S. operators is estimated to be $1,380, or $60 per 
airplane, per inspection cycle.
    It would take approximately 14 work hours per airplane to 
accomplish the proposed replacement and reidentification, at an average 
labor rate of $60 per work hour. The manufacturer has committed 
previously to its customers that it will bear the cost of replacement 
parts. As a result, the cost of those parts is not attributable to this 
proposed AD. Based on these figures, the cost impact of the replacement 
and reidentification proposed by this AD on U.S. operators is estimated 
to be $19,320, or $840 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 proposed AD were not adopted. The cost impact 
figures discussed in AD rulemaking actions represent only the time 
necessary to perform the specific actions actually required by the AD. 
These figures typically do not include incidental costs, such as the 
time required to gain access and close up,

[[Page 26819]]

planning time, or time necessitated by other administrative actions.

Regulatory Impact

    The regulations proposed herein would not have a substantial direct 
effect 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, it 
is determined that this proposal would not have federalism implications 
under Executive Order 13132.
    For the reasons discussed above, I certify that this proposed 
regulation (1) is not a ``significant regulatory action'' under 
Executive Order 12866; (2) is not a ``significant rule'' under the DOT 
Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 
and (3) if promulgated, 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 copy of the draft 
regulatory evaluation prepared for this action is contained in the 
Rules Docket. A copy of it may be obtained by contacting the Rules 
Docket at the location provided under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration proposes to amend 
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:

McDonnell Douglas: Docket 2001-NM-47-AD.

    Applicability: Model 717 series airplanes, manufacturer's 
fuselage numbers 5004 through 5036 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 (c) 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 rod ends of the spoiler hold-down 
actuators due to fatigue, which could result in loss of the back-up 
protection of the spoiler float hold-down and unavailability of 
monitoring for an uncommanded spoiler movement, accomplish the 
following:

General Visual Inspection

    (a) Within 450 flight hours after the effective date of this AD, 
do a general visual inspection of the rod ends of the spoiler hold-
down actuators of the inboard and outboard spoilers for breakage 
along the intersection of the thread runout and the outer spherical 
surface of the lug, per Boeing Alert Service Bulletin 717-27A0010, 
dated August 15, 2000.

    Note 2: For the purposes of this AD, a general visual inspection 
is defined as ``A visual examination of an interior or exterior 
area, installation, or assembly to detect obvious damage, failure, 
or irregularity. This level of inspection is made under normally 
available lighting conditions such as daylight, hangar lighting, 
flashlight, or drop-light, and may require removal or opening of 
access panels or doors. Stands, ladders, or platforms may be 
required to gain proximity to the area being checked.''

Condition 1 (No Breakage Present)

    (1) If no breakage is present, repeat the general visual 
inspection every 450 flight hours.

Condition 2 (Breakage Present)

    (2) If any breakage is present, before further flight, replace 
the broken rod end of the spoiler hold-down actuator with a new rod 
end, per Boeing Alert Service Bulletin 717-27A0010, dated August 15, 
2000; or Boeing Service Bulletin 717-27-0013, dated January 30, 
2001, or Revision 01, dated February 28, 2001. As of the effective 
date of this AD, the replacement shall be done per Boeing Service 
Bulletin 717-27-0013, Revision 01, dated February 28, 2001. For rod 
ends that have been replaced per Boeing Alert Service Bulletin 717-
27A0010, dated August 15, 2000, repeat the general visual inspection 
thereafter every 450 flight hours. Accomplishment of this 
replacement per Boeing Service Bulletin 717-27-0013 constitutes 
terminating action for the requirements of this AD for that rod end.

Terminating Action

    (b) Within 15 months or 3,600 flight hours after the effective 
date of this AD, whichever occurs first, replace the rod ends of the 
spoiler hold-down actuators with new rod ends, and reidentify the 
spoiler hold-down actuators, per Boeing Service Bulletin 717-27-
0013, dated January 30, 2001, or Revision 01, dated February 28, 
2001. Accomplishment of this replacement and reidentification 
constitutes terminating action for the requirements of this AD.

Alternative Methods of Compliance

    (c) 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, Los Angeles Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

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

Special Flight Permit

    (d) 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.

    Issued in Renton, Washington, on May 9, 2001.
Donald L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-12176 Filed 5-14-01; 8:45 am]
BILLING CODE 4910-13-P