Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes, 14463-14465 [E9-7001]

Download as PDF Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations 14463 Actions Compliance Procedures (1) Insert the following into the Limitations section of the airplane flight manual (AFM): ‘‘Operate Only under Day Visual Flight Rules (VFR).’’ You may remove the limitations specified in this paragraph after doing the action required in paragraphs (e)(2) and (e)(3) of this AD, as applicable. Before further flight after May 5, 2009 (the effective date of this AD). (2) Inspect the 35-amp and 250-amp current limiters for installation in the proper location. (3) If you find any current limiter not in the proper location, reinstall the current limiter in the proper location. Within 100 hours time-in-service after May 5, 2009 (the effective date of this AD). Before further flight after the inspection required in paragraph (e)(2) of this AD. Under 14 CFR 43.7, the owner/operator holding at least a private pilot certificate is allowed to insert the information into the AFM as specified in paragraph (e)(1) of this AD. You may insert a copy of this AD into the Limitations section of the AFM to comply with this action. Make an entry into the aircraft logbook showing compliance with this portion of the AD per compliance with 14 CFR 43.9. Follow Piper Aircraft, Inc. Service Bulletin No. 2000, dated September 16, 2008. Follow Piper Aircraft, Inc. Service Bulletin No. 2000, dated September 16, 2008. Alternative Methods of Compliance (AMOCs) (f) The Manager, Atlanta Aircraft Certification Office (ACO), 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: John Lee, Aerospace Engineer, One Crown Center, 1895 Phoenix Blvd., Suite 450, Atlanta, Georgia 30349; telephone: (770) 994–6736; fax: (770) 703–6097. 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. tjames on PRODPC61 with RULES Material Incorporated by Reference (g) You must use Piper Aircraft, Inc. Service Bulletin No. 2000, dated September 16, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 978–6573; Internet: https:// www.newpiper.com/company/ publications.asp. (3) You may review copies of the service information incorporated by reference for this AD at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the Central Region, call (816) 329–3768. (4) You may also review copies of the service information incorporated by reference for this AD at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. VerDate Nov<24>2008 14:33 Mar 30, 2009 Jkt 217001 Issued in Kansas City, Missouri, on March 24, 2009. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–6986 Filed 3–30–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1155; Directorate Identifier 2008–NM–146–AD; Amendment 39–15866; AD 2009–07–07] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model 717–200 Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717–200 airplanes. This AD requires modifying the wire installation of the auxiliary hydraulic pump in the right wheel well of the main landing gear (MLG). This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent a tire burst when the MLG is in the retracted position from causing damage to the wire assembly of the auxiliary hydraulic pump and subsequent electrical arcing, creating the potential of an ignition source to the center wing tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. DATES: This AD is effective May 5, 2009. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 of a certain publication listed in the AD as of May 5, 2009. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. The service information is also available at https://www.regulations.gov. 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin Safety/Mechanical and Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5353; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to certain McDonnell Douglas Model 717– 200 airplanes. That NPRM was E:\FR\FM\31MRR1.SGM 31MRR1 14464 Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations published in the Federal Register on October 31, 2008 (73 FR 64892). That NPRM proposed to require modifying the wire installation of the auxiliary hydraulic pump in the right wheel well of the main landing gear. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. tjames on PRODPC61 with RULES Request To Reduce Compliance Time The Air Line Pilots Association, International (ALPA), asks that the compliance time for the modification in the NPRM be reduced. ALPA states that the 60-month compliance time is excessive given the potential consequences and adds that, since the wiring modification is estimated to take only 11 work hours per airplane, a shorter compliance time is recommended. ALPA suggests the compliance time be reduced to 24 months. We do not agree to reduce the compliance time required by this AD. The compliance time was part of a Special Federal Aviation Regulation No. 88 (SFAR 88) safety analysis that consisted of a total package of mandated actions for each airplane model. The probability of failure and the burden on operators were considered when developing and applying consistent compliance times to all SFAR 88 rulemaking actions. In developing the 60-month compliance time for this AD action, we also considered not only the safety implications of the identified unsafe condition, but the average utilization rate of the affected fleet, and the practical aspects of an orderly modification of the fleet during regular maintenance periods. In addition, we considered the manufacturer’s recommendation for an appropriate compliance time. After considering all the available information, we determined that performing the actions within 60 months represents an appropriate interval of time in which the required actions can be performed in a timely manner within the affected fleet, while still maintaining an adequate level of safety. In addition, operators can always comply with the required actions earlier than the compliance time in the AD. We have made no change to the AD in this regard. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting the AD as proposed. VerDate Nov<24>2008 14:33 Mar 30, 2009 Jkt 217001 Costs of Compliance Adoption of the Amendment We estimate that this AD affects 8 airplanes of U.S. registry. We also estimate that it takes 11 work-hours per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts cost is minimal. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $7,040, or $880 per product. ■ Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ 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 This AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: (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. 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, Incorporation by reference, Safety. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–07–07 McDonnell Douglas: Amendment 39–15866. Docket No. FAA–2008–1155; Directorate Identifier 2008–NM–146–AD. Effective Date (a) This airworthiness directive (AD) is effective May 5, 2009. 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 717–29A0009, dated July 31, 2008. Unsafe Condition (d) This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent a tire burst when the main landing gear (MLG) is in the retracted position from causing damage to the wire assembly of the auxiliary hydraulic pump and subsequent electrical arcing, creating the potential of an ignition source to the center wing tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. Compliance (e) Comply with this AD within the compliance times specified, unless already done. Installation/Re-Routing (f) Within 60 months after the effective date of this AD: Modify the wire installation of the auxiliary hydraulic pump in the right wheel well of the MLG by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 717–29A0009, dated July 31, 2008. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Los Angeles Aircraft Certification Office, FAA, ATTN: Ken Sujishi, Aerospace Engineer, Cabin Safety/ Mechanical and Environmental Systems Branch, ANM–150L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712– 4137; telephone (562) 627–5353; fax (562) E:\FR\FM\31MRR1.SGM 31MRR1 Federal Register / Vol. 74, No. 60 / Tuesday, March 31, 2009 / Rules and Regulations 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. Material Incorporated by Reference (h) You must use Boeing Alert Service Bulletin 717–29A0009, dated July 31, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, California 90846– 0001; telephone 206–544–5000, extension 2; fax 206–766–5683; e-mail dse.boecom@boeing.com; Internet https:// www.myboeingfleet.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. The service information is also available at https:// www.regulations.gov. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on March 17, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–7001 Filed 3–30–09; 8:45 am] tjames on PRODPC61 with RULES BILLING CODE 4910–13–P VerDate Nov<24>2008 14:33 Mar 30, 2009 Jkt 217001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23646; Directorate Identifier 2006–CE–005–AD; Amendment 39–15849; AD 2006–08–08 R1] RIN 2120–AA64 Airworthiness Directives; Air Tractor, Inc. Models AT–400, AT–401, AT–401B, AT–402, AT–402A, and AT–402B Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) to revise AD 2006–08–08, which applies to certain Air Tractor, Inc. (Air Tractor) Models AT–400, AT–401, AT–401B, AT–402, AT–402A, and AT–402B airplanes. AD 2006–08–08 currently requires you to repetitively eddy current inspect the wing lower spar cap in order to reach the safe life and, for certain Models AT–402A and AT–402B airplanes and those that incorporate or have incorporated Marburger Enterprises, Inc. (Marburger) winglets, lowers the safe life for the wing lower spar cap. Since we issued AD 2006–08– 08, we have received information to update inspection intervals for the Models AT–401B, AT–402A, and AT– 402B airplanes based on a revised damage tolerance analysis. Consequently, this AD would not only retain the actions of AD 2006–08–08, but would reduce the number of repetitive inspections for all affected Model AT–401B airplanes and certain Models AT–402A and AT–402B airplanes. We are issuing this AD to prevent fatigue cracks from occurring in the wing lower spar cap before the originally established safe life is reached. Fatigue cracks in the wing lower spar cap, if not detected and corrected, could result in wing separation and loss of control of the airplane. DATES: This AD becomes effective on May 5, 2009. As of April 21, 2006 (71 FR 19986, April 19, 2006), the Director of the Federal Register approved the incorporation by reference of Snow Engineering Co. Drawing 21088, dated November 3, 2004; Snow Engineering Co. Process Specification 197, page 1, revised June 4, 2002, pages 2 through 4, dated February 23, 2001, and page 5, dated May 3, 2002; and Snow PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 14465 Engineering Co. Service Letter 202, page 3, dated October 16, 2000, listed in this AD. ADDRESSES: For service information identified in this AD, contact Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374; telephone: (940) 564–5616; facsimile: (940) 564–5612; Internet: https://www.airtractor.com; or Marburger Enterprises, Inc., 1227 Hillcourt, Williston, North Dakota 58801; telephone: (800) 893–1420 or (701) 774–0230; facsimile: (701) 572– 2602. To view the AD docket, go to U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, or on the Internet at https:// www.regulations.gov. The docket number is FAA–2006–23646; Directorate Identifier 2006–CE–005–AD. FOR FURTHER INFORMATION CONTACT: Direct all questions to: —For airplanes that do not incorporate and never have incorporated Marburger winglets: Rob Romero, Aerospace Engineer, FAA, Fort Worth Airplane Certification Office, 2601 Meacham Boulevard, Fort Worth, Texas 76193–0150; telephone: (817) 222–5102; facsimile: (817) 222–5960; and —For airplanes that incorporate or have incorporated Marburger Enterprises, Inc. winglets: John Cecil, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 3960 Paramount Boulevard, Lakewood, California 90712; telephone: (562) 627–5228; facsimile: (562) 627–5210. SUPPLEMENTARY INFORMATION: Discussion On December 4, 2008, we issued a proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Air Tractor Models AT–400, AT–401, AT–401B, AT–402, AT–402A, and AT–402B airplanes. This proposal was published in the Federal Register as a notice of proposed rulemaking (NPRM) on December 10, 2008 (73 FR 74999). The NPRM proposed to revise AD 2006–08–08 with a new AD that would not only retain the actions of AD 2006–08–08, but would reduce the number of repetitive inspections for all affected Model AT–401B airplanes and certain Models AT–402A and AT–402B airplanes. The following table contains AD actions that address the wing spar safe life of the Air Tractor airplane fleet: E:\FR\FM\31MRR1.SGM 31MRR1

Agencies

[Federal Register Volume 74, Number 60 (Tuesday, March 31, 2009)]
[Rules and Regulations]
[Pages 14463-14465]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-7001]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1155; Directorate Identifier 2008-NM-146-AD; 
Amendment 39-15866; AD 2009-07-07]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717-200 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
McDonnell Douglas Model 717-200 airplanes. This AD requires modifying 
the wire installation of the auxiliary hydraulic pump in the right 
wheel well of the main landing gear (MLG). This AD results from fuel 
system reviews conducted by the manufacturer. We are issuing this AD to 
prevent a tire burst when the MLG is in the retracted position from 
causing damage to the wire assembly of the auxiliary hydraulic pump and 
subsequent electrical arcing, creating the potential of an ignition 
source to the center wing tank, which, in combination with flammable 
fuel vapors, could result in a fuel tank explosion and consequent loss 
of the airplane.

DATES: This AD is effective May 5, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 5, 2009.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. The 
service information is also available at https://www.regulations.gov.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document Management 
Facility, U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Ken Sujishi, Aerospace Engineer, Cabin 
Safety/Mechanical and Environmental Systems Branch, ANM-150L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5353; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an airworthiness directive (AD) that would apply to 
certain McDonnell Douglas Model 717-200 airplanes. That NPRM was

[[Page 14464]]

published in the Federal Register on October 31, 2008 (73 FR 64892). 
That NPRM proposed to require modifying the wire installation of the 
auxiliary hydraulic pump in the right wheel well of the main landing 
gear.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Reduce Compliance Time

    The Air Line Pilots Association, International (ALPA), asks that 
the compliance time for the modification in the NPRM be reduced. ALPA 
states that the 60-month compliance time is excessive given the 
potential consequences and adds that, since the wiring modification is 
estimated to take only 11 work hours per airplane, a shorter compliance 
time is recommended. ALPA suggests the compliance time be reduced to 24 
months.
    We do not agree to reduce the compliance time required by this AD. 
The compliance time was part of a Special Federal Aviation Regulation 
No. 88 (SFAR 88) safety analysis that consisted of a total package of 
mandated actions for each airplane model. The probability of failure 
and the burden on operators were considered when developing and 
applying consistent compliance times to all SFAR 88 rulemaking actions. 
In developing the 60-month compliance time for this AD action, we also 
considered not only the safety implications of the identified unsafe 
condition, but the average utilization rate of the affected fleet, and 
the practical aspects of an orderly modification of the fleet during 
regular maintenance periods. In addition, we considered the 
manufacturer's recommendation for an appropriate compliance time. After 
considering all the available information, we determined that 
performing the actions within 60 months represents an appropriate 
interval of time in which the required actions can be performed in a 
timely manner within the affected fleet, while still maintaining an 
adequate level of safety. In addition, operators can always comply with 
the required actions earlier than the compliance time in the AD. We 
have made no change to the AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

Costs of Compliance

    We estimate that this AD affects 8 airplanes of U.S. registry. We 
also estimate that it takes 11 work-hours per product to comply with 
this AD. The average labor rate is $80 per work-hour. Required parts 
cost is minimal. Based on these figures, we estimate the cost of this 
AD to the U.S. operators to be $7,040, or $880 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 that this AD:
    (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.
    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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2009-07-07 McDonnell Douglas: Amendment 39-15866. Docket No. FAA-
2008-1155; Directorate Identifier 2008-NM-146-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective May 5, 2009.

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 717-29A0009, dated July 31, 2008.

Unsafe Condition

    (d) This AD results from fuel system reviews conducted by the 
manufacturer. We are issuing this AD to prevent a tire burst when 
the main landing gear (MLG) is in the retracted position from 
causing damage to the wire assembly of the auxiliary hydraulic pump 
and subsequent electrical arcing, creating the potential of an 
ignition source to the center wing tank, which, in combination with 
flammable fuel vapors, could result in a fuel tank explosion and 
consequent loss of the airplane.

Compliance

    (e) Comply with this AD within the compliance times specified, 
unless already done.

Installation/Re-Routing

    (f) Within 60 months after the effective date of this AD: Modify 
the wire installation of the auxiliary hydraulic pump in the right 
wheel well of the MLG by doing all the applicable actions specified 
in the Accomplishment Instructions of Boeing Alert Service Bulletin 
717-29A0009, dated July 31, 2008.

Alternative Methods of Compliance (AMOCs)

    (g)(1) The Manager, Los Angeles Aircraft Certification Office, 
FAA, ATTN: Ken Sujishi, Aerospace Engineer, Cabin Safety/Mechanical 
and Environmental Systems Branch, ANM-150L, FAA, Los Angeles 
Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, 
California 90712-4137; telephone (562) 627-5353; fax (562)

[[Page 14465]]

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.

Material Incorporated by Reference

    (h) You must use Boeing Alert Service Bulletin 717-29A0009, 
dated July 31, 2008, to do the actions required by this AD, unless 
the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-
0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail 
dse.boecom@boeing.com; Internet https://www.myboeingfleet.com.
    (3) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152. The service information 
is also available at https://www.regulations.gov.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 17, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E9-7001 Filed 3-30-09; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.