Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes, 18725-18727 [E8-7183]

Download as PDF Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules instructions and replace before further flight. If MLG Rib 5 is not replaced in accordance with the instructions defined in Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007; repeat the applicable inspection in paragraph (g) of this AD at the time specified in the applicable paragraph. (4) If any crack is detected during the ultrasonic inspection required by paragraph (g) of this AD, before further flight, accomplish the actions specified in paragraphs (g)(4)(i) or (g)(4)(ii) of this AD, as applicable. (i) If any crack is not visible on MLG Rib 5: Before further flight, repair MLG Rib 5 using Repair Instruction R572–49121, Issue C, dated May 2007. After embodiment of Repair Instruction R572–49121, no further actions are required by this AD and Airbus Service Bulletin A310–57–2091, including Appendix 01, dated May 22, 2007, for that MLG Rib 5 only. (ii) If any crack is visible on MLG Rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. If MLG Rib 5 is not replaced in accordance with the instructions defined in Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007, repeat the applicable inspection in paragraph (g) of this AD at the time specified. Accomplishing the replacement defined in Airbus Service Bulletin A310–57–2090 ends the repetitive inspections required by paragraph (g)(1) of this AD for that MLG Rib 5 only. FAA AD Differences rfrederick on PROD1PC67 with PROPOSALS Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. 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. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority 15:07 Apr 04, 2008 Related Information (i) Refer to MCAI EASA Airworthiness Directive 2007–0195, dated July 19, 2007, and Airbus Service Bulletins A310–57–2090, Revision 01, dated December 19, 2007, and A310–57–2091, including Appendix 01, dated May 22, 2007, for related information. Issued in Renton, Washington, on March 27, 2008. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–7163 Filed 4–4–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Jkt 214001 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 https://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). 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2008–0407; Directorate Identifier 2008–NM–002–AD] You may examine the AD docket on the Internet at https:// 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: RIN 2120–AA64 Note 2: This AD differs from the MCAI and/or service information as follows: Although the MCAI or service information allows flight with cracks on aft bearing forward lugs for a certain period of time, this AD requires replacing MLG Rib 5 before further flight if any crack is found. Although the MCAI or service information specifies submitting an inspection report sheet to Airbus, this AD would not require that action. VerDate Aug<31>2005 (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. 18725 Airworthiness Directives; McDonnell Douglas Model 717–200 Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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 PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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 E:\FR\FM\07APP1.SGM 07APP1 18726 Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules proposed AD because of those comments. We will post all comments we receive, without change, to https:// 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. rfrederick on PROD1PC67 with PROPOSALS 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 pullpull 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 VerDate Aug<31>2005 15:07 Apr 04, 2008 Jkt 214001 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 workhour. 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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. § 39.13 [Amended] 2. The FAA amends § 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. E:\FR\FM\07APP1.SGM 07APP1 Federal Register / Vol. 73, No. 67 / Monday, April 7, 2008 / Proposed Rules 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 FEDERAL TRADE COMMISSION 16 CFR Part 303 Rules and Regulations Under the Textile Fiber Products Identification Act Federal Trade Commission. Reopening of comment period. rfrederick on PROD1PC67 with PROPOSALS AGENCY: ACTION: The Federal Trade Commission (‘‘Commission’’ or ‘‘FTC’’), pursuant to a Petition filed by Mohawk Industries, Inc. (‘‘Mohawk’’), E. I. du Pont de Nemours and Company SUMMARY: VerDate Aug<31>2005 15:07 Apr 04, 2008 Jkt 214001 (‘‘DuPont’’), and PTT Poly Canada (‘‘PTT Canada’’) (hereinafter ‘‘Petitioners’’), solicited comments on whether the Commission should: amend Rule 7(c) of the Rules and Regulations Under the Textile Fiber Products Identification Act (‘‘Textile Rules’’) to establish a new generic fiber subclass name and definition within the existing definition of ‘‘polyester’’ for a specifically proposed subclass of polyester fibers made from poly(trimethylene terephthalate) (‘‘PTT’’); amend Rule 7(c) to broaden or clarify its definition of ‘‘polyester’’ to describe more accurately the PTT fiber; or retain Rule 7(c)’s definition of ‘‘polyester.’’ The Commission received comments through November 12, 2007. Based on those comments, the Commission is reopening the comment period for an additional 30 days. DATES: Comments will be accepted until May 5, 2008. ADDRESSES: Comments should refer to ‘‘16 CFR Part 303—Textile Rule 8, Mohawk, DuPont, and PTT Canada Comment, Matter No. P074201’’ to facilitate the organization of comments. A comment filed in paper form should include this reference both in the text and on the envelope, and should be mailed or delivered to the following address: Federal Trade Commission/ Office of the Secretary, Room H-135 (Annex K), 600 Pennsylvania Avenue, NW., Washington, DC 20580. Because paper mail in the Washington area and at the FTC is subject to delay, please consider submitting your comment in electronic form, as prescribed below. Comments containing any material for which confidential treatment is requested, however, must be filed in paper (rather than electronic) form, and the first page of the document must be clearly labeled ‘‘Confidential,’’ and must comply with Commission Rule 4.9(c).1 The FTC is requesting that any comment filed in paper form be sent by courier or overnight service, if possible, because postal mail in the Washington area and at the Commission is subject to delay due to heightened security precautions. Comments filed in electronic form (except comments containing any confidential material) should be submitted to the FTC by clicking on the following Web link: https:// 1 The comment must be accompanied by an explicit request for confidential treatment, including the factual and legal basis for the request, and must identify the specific portions of the comment to be withheld from the public record. The request will be granted or denied by the Commission’s General Counsel, consistent with applicable law and the public interest. See Commission Rule 4.9(c), 16 CFR 4.9(c). PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 18727 secure.commentworks.com/ftc-Mohawk, DuPontandPTTCanadaComment and following the instructions on the Webbased form. You may also visit https:// www.regulations.gov to read this request for public comment, and may file an electronic comment through that Web site. The FTC will consider all comments that www.regulations.gov forwards to it. The FTC Act and other laws the Commission administers permit the collection of public comments to consider and use in this proceeding as appropriate. All timely and responsive public comments, whether filed in paper or electronic form, will be available to the public on the FTC Web site, to the extent practicable, at https:// www.ftc.gov/os/publiccomments.shtm. As a matter of discretion, the FTC makes every effort to remove home contact information for individuals from the public comments it receives before placing those comments on the FTC Web site. More information, including routine uses permitted by the Privacy Act, may be found in the FTC’s privacy policy at https://www.ftc.gov/ftc/ privacy.htm. FOR FURTHER INFORMATION CONTACT: Janice Podoll Frankle, Attorney, Division of Enforcement, Bureau of Consumer Protection, Federal Trade Commission, Washington, DC 20580; (202) 326-3022. SUPPLEMENTARY INFORMATION: In a Federal Register Notice,2 the Commission solicited comments on whether to amend Rule 7(c) of the Rules and Regulations Under the Textile Fiber Products Identification Act (‘‘Textile Rules’’) to establish a new generic fiber subclass name and definition within the existing definition of ‘‘polyester.’’ Specifically, the Commission asked whether it should establish a new subclass of polyester fibers made from PTT. At the close of the comment period on November 12, 2007, the Commission had received 49 comments.3 With the exception of one comment, from INVISTA S. r.l. (‘‘INVISTA’’),4 all of the commenters stated that they favored amending the Textile Rules to add a generic fiber subclass designation for PTT. The Commission received INVISTA’s comment opposing the Petition three days prior to the close of the 75 day comment period. Thus, the public had 72 Fed. Reg. 48,600 (Aug. 24, 2007). The 49 comments can be found at: https:// www.ftc.gov/os/comments/textile-mohawk/ index.shtm 4 INVISTA’s comment can be found at: https:// www.ftc.gov/os/comments/textile-mohawk/53204700053.pdf 2 3 E:\FR\FM\07APP1.SGM 07APP1

Agencies

[Federal Register Volume 73, Number 67 (Monday, April 7, 2008)]
[Proposed Rules]
[Pages 18725-18727]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-7183]


-----------------------------------------------------------------------

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 https://
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 https://
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 https://
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

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