[Federal Register: April 7, 2008 (Volume 73, Number 67)]
[Proposed Rules]
[Page 18725-18727]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07ap08-15]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0407; Directorate Identifier 2008-NM-002-AD]
RIN 2120-AA64
Airworthiness Directives; McDonnell Douglas Model 717-200
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain McDonnell Douglas Model 717-200 airplanes. This proposed AD
would require inspecting the drive assembly of the aft elevator standby
loop for interference between the clevis and bolt of the bellcrank
assembly, correct orientation of the pull-pull cable clevis bolt, and
excessive freeplay of the bellcrank assembly bearing, and corrective
actions if necessary. This proposed AD would also require modifying the
pull-pull cable clevis in the drive assembly of the aft elevator
standby loop for certain airplanes. This proposed AD results from a
report of an aborted takeoff due to a control column disconnect. We are
proposing this AD to prevent binding of the bolt that connects the
cable 264A clevis to the bellcrank assembly against the adjacent
(upper) clevis of the pull-pull cable assembly. This binding condition
could result in slow airplane rotation or a control column disconnect
during takeoff and a runway excursion if takeoff must be aborted.
DATES: We must receive comments on this proposed AD by May 22, 2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Boeing
Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard,
Long Beach, California 90846, Attention: Data and Service Management,
Dept. C1-L5A (D800-0024).
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: David Rathfelder, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137;
telephone (562) 627-5229; fax (562) 627-5210.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0407;
Directorate Identifier 2008-NM-002-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this
[[Page 18726]]
proposed AD because of those comments.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We received a report of an aborted takeoff due to a control column
disconnect. A cable in the fuselage drive assembly of the aft elevator
standby loop was in intermittent contact with the adjacent clevis.
Investigation revealed that the bolt connecting the cable 264A clevis
to the bellcrank assembly within the drive assembly of the aft elevator
standby loop may bind against the adjacent upper clevis of the pull-
pull cable assembly. Further investigation revealed that one of the
bolts of the drive assembly of the aft elevator standby loop and pull-
pull cable clevis might be installed ``head up'' adding to the
potential binding condition. The ``head up'' installation is not in
accordance with design requirements. In addition, the bellcrank bearing
had excessive freeplay due to corrosion that contributed to the binding
condition. This binding condition, if not corrected, could result in
slow airplane rotation or a control column disconnect during takeoff
and a runway excursion if takeoff must be aborted.
Relevant Service Information
We have reviewed Boeing Alert Service Bulletin 717-27A0039, dated
December 6, 2007. The service bulletin describes procedures for a
general visual inspection of the drive assembly of the aft elevator
standby loop for interference between the clevis and bolt of the
bellcrank assembly, correct orientation of the pull-pull cable clevis
bolt, and excessive freeplay of the bellcrank assembly bearing, and
corrective actions if necessary. The service bulletin also describes
procedures for modifying the pull-pull cable clevis in the drive
assembly of the aft elevator standby loop on certain airplanes. If any
interference, incorrect orientation, or excessive freeplay is found,
the corrective actions include rotating cable segment 264A, changing
the bellcrank assembly bearing, and rotating the pull-pull cable
clevis.
For Group 1, Configuration 1 and 2: The compliance time for
performing the inspection is within 3,000 flight hours or 27 months
after the service bulletin date, whichever occurs first. For Group 1,
Configuration 1: The compliance time for accomplishing the modification
is within 27 months after the service bulletin date.
FAA's Determination and Requirements of This Proposed AD
We are proposing this AD because we evaluated all relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
This proposed AD would require accomplishing the actions specified in
the service information described previously.
Costs of Compliance
We estimate that this proposed AD would affect 123 airplanes of
U.S. registry.
It would take about 1 work-hour per product to do the proposed
inspection. The average labor rate is $80 per work-hour. Based on these
figures, we estimate the cost of this proposed AD to the U.S. operators
to be $9,840, or $80 per product.
It would take about 4 work-hours per product to do the proposed
modification. Required parts would cost about $163 per product. Based
on these figures, we estimate the cost of this proposed AD to the U.S.
operators to be $59,409, or $483 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify 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. 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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
McDonnell Douglas: Docket No. FAA-2008-0407; Directorate Identifier
2008-NM-002-AD.
Comments Due Date
(a) We must receive comments by May 22, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to McDonnell Douglas Model 717-200
airplanes, certificated in any category, as identified in Boeing
Alert Service Bulletin 717-27A0039, dated December 6, 2007.
Unsafe Condition
(d) This AD results from a report of an aborted takeoff due to a
control column disconnect. We are issuing this AD to prevent binding
of the bolt that connects the cable 264A clevis to the bellcrank
assembly against the adjacent (upper) clevis of the pull-pull cable
assembly. This binding condition could result in slow airplane
rotation or a control column disconnect during takeoff and a runway
excursion if takeoff must be aborted.
Compliance
(e) Comply with this AD within the compliance times specified,
unless already done.
[[Page 18727]]
Inspection/Corrective Actions
(f) At the applicable time specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 717-27A0039, dated
December 6, 2007; except, where the service bulletin specifies a
compliance time after the date on the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD: Do the applicable actions specified in
paragraphs (f)(1) and (f)(2) of this AD in accordance with the
Accomplishment Instructions of the service bulletin.
(1) For all airplanes: Do a general visual inspection of the
drive assembly of the aft elevator standby loop for interference
between the clevis and bolt of the bellcrank assembly, correct
orientation of the pull-pull cable clevis bolt, and excessive
freeplay of the bellcrank assembly bearing. Do all applicable
corrective actions before further flight.
(2) For airplanes identified in the service bulletin as Group 1,
Configuration 1: Modify the pull-pull cable clevis in the drive
assembly of the aft elevator standby loop.
Alternative Methods of Compliance (AMOCs)
(g)(1) The Manager, Los Angeles Aircraft Certification Office
(ACO), FAA, ATTN: David Rathfelder, Aerospace Engineer, Airframe
Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard,
Lakewood, California 90712-4137; telephone (562) 627-5229; fax (562)
627-5210; has the authority to approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
Issued in Renton, Washington, on March 28, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-7183 Filed 4-4-08; 8:45 am]
BILLING CODE 4910-13-P