
[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]                         

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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).

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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
