Airworthiness Directives; McDonnell Douglas Model 717-200 Airplanes, 30615-30617 [05-10428]

Download as PDF Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations 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 the 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. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 2005–NE–15– AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I 2005–11–01 Turbomeca S.A.: Amendment 39–14103. Docket No. FAA–2005–21273; Directorate Identifier 2005–NE–15–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 13, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 1A turboshaft engines. These engines are installed on, but not limited to, Eurocopter AS355N Twinstar helicopters. Unsafe Condition (d) This AD results from an investigation into the Digital Electronic Control Unit (DECU) that revealed a malfunction of the Free Turbine Overspeed Protection System can exist despite the DECU passing all functional tests specified in the Engine VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 Compliance Issued in Burlington, Massachusetts, on May 17, 2005. Robert E. Guyotte, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–10295 Filed 5–26–05; 8:45 am] (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. BILLING CODE 4910–13–P Initial Testing DEPARTMENT OF TRANSPORTATION (f) Within 25 flight hours after the effective date of this AD, test the DECU Free Turbine Overspeed Protection System, using paragraph 2.B. of the Instructions to be Incorporated of Turbomeca Alert Mandatory Service Bulletin No. A319 77 0804, dated March 24, 2005. (g) If the DECU Free Turbine Overspeed Protection System fails the test specified in paragraph (f) of this AD, replace the DECU before further flight. Federal Aviation Administration Repetitive Testing (h) Repeat the testing specified in paragraph (f) of this AD at each functional test of the DECU Free Turbine Overspeed Protection System. Information on the functional tests of the DECU Free Turbine Overspeed Protection System can be found in the Engine Maintenance Manual, Section 77– 30–01. Recommended intervals for the functional test of the Turbine Overspeed Protection System can be found in the Engine Maintenance Manual, Section 05–10–02. Alternative Methods of Compliance (i) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. PART 39—AIRWORTHINESS DIRECTIVES § 39.13 Maintenance Manual. We are issuing this AD to prevent uncontained engine failure in the event of a free turbine overspeed. 30615 Related Information (j) DGAC airworthiness directive F–2005– 063, dated April 27, 2005, and UF–2005, 063 R1, dated May 4, 2005, also address the subject of this AD. Material Incorporated by Reference (k) You must use Turbomeca Alert Mandatory Service Bulletin No. A319 77 0804, dated March 24, 2005, to perform the tests required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001, on the Internet at https://dms.dot.gov; or 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. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 14 CFR Part 39 [Docket No. FAA–2004–19987; Directorate Identifier 2004–NM–203–AD; Amendment 39–14105; AD 2005–11–03] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Model 717–200 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717–200 airplanes. This AD requires replacing eight brake fuses of the hydraulic quantity limiter with new or modified and reidentified fuses. This AD is prompted by reports indicating that brake fuses of the hydraulic quantity limiter of the main landing gear have failed. We are issuing this AD to prevent loss of both hydraulic and brake systems if one fuse on each hydraulic system were to fail simultaneously, and consequent reduced controllability of the airplane. DATES: This AD becomes effective July 1, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of July 1, 2005. ADDRESSES: 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). Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at E:\FR\FM\27MYR1.SGM 27MYR1 30616 Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations the U.S. Department of Transportation, 400 Seventh Street SW, room PL–401, Washington, DC. This docket number is FAA–2004–19987; the directorate identifier for this docket is 2004–NM– 203–AD. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments that have been submitted on the proposed AD. FOR FURTHER INFORMATION CONTACT: Support for Proposed AD One commenter supports the proposed AD. Albert Lam, 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) 627–5346; fax (562) 627–5210. The FAA proposed to amend 14 CFR part 39 with an AD for certain McDonnell Douglas Model 717–200 airplanes. That action, published in the Federal Register on January 5, 2005 (70 FR 731), proposed to require replacing eight brake fuses of the hydraulic quantity limiter with new or modified and reidentified fuses. SUPPLEMENTARY INFORMATION: paragraph 2.C.1. of the service bulletin identifies the vendor part numbers that correspond to the Boeing part numbers referenced in the AD. Therefore, we find it unnecessary to specify vendor part numbers in either paragraph (g) or (h) of the AD when the referenced service bulletin contains that information. We have made no change to the AD in this regard. Request to Refer to Vendor Part Numbers One commenter has no technical objection to the proposed AD, but would like the vendor part numbers to be included with the Boeing part numbers in paragraphs (g) and (h) of the proposed AD. The commenter provided no justification for its request. We do not agree. Paragraph (g) of the AD refers to Boeing Alert Service Bulletin 717–32A0031, dated September 10, 2004, as the appropriate source of service information for accomplishing the required replacement. Note (a) of Conclusion We have carefully reviewed the available data, including the comments that have been submitted, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 133 airplanes of the affected design in the worldwide fleet and 103 airplanes on the U.S. registry. The following table provides the estimated costs for U.S. operators to comply with this AD. ESTIMATED COSTS Action Work hours Option 1. Replacement with new brake fuses ................................................... Option 2. Replacement with modified and reidentified brake fuses .................. 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 have determined that 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 VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 9 13 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. We prepared a regulatory evaluation of the estimated costs to comply with this AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Average labor rate per hour $65 65 Parts No Charge ... No Charge ... Cost per airplane $585 845 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): I 2005–11–03 McDonnell Douglas: Amendment 39–14105. Docket No. FAA– 2004–19987; Directorate Identifier 2004– NM–203–AD. Effective Date (a) This AD becomes effective July 1, 2005. Affected ADs (b) None. Applicability (c) This AD applies to McDonnell Douglas Model 717–200 airplanes, fuselage numbers 5002 through 5134 inclusive; certificated in any category. Unsafe Condition (d) This AD was prompted by reports indicating that brake fuses of the hydraulic quantity limiter of the main landing gear (MLG) have failed. We are issuing this AD to prevent loss of both hydraulic and brake systems if one fuse on each hydraulic system E:\FR\FM\27MYR1.SGM 27MYR1 Federal Register / Vol. 70, No. 102 / Friday, May 27, 2005 / Rules and Regulations were to fail simultaneously, and consequent reduced controllability of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. 30617 Compliance Times (f) At the applicable time in Table 1 of this AD, do the action required by paragraph (g) of this AD. TABLE 1.—COMPLIANCE TIMES For airplanes having— Compliance time (1) Less than 5,000 total flight cycles as of the effective date of this AD (2) 5,000 or more total flight cycles as of the effective date of this AD .. Replacement (g) Replace the eight brake fuses of the hydraulic quantity limiter by doing either Option 1 or Option 2 in Table 2 of this AD in accordance with Boeing Alert Service Bulletin 717–32A0031, dated September 10, 2004. TABLE 2.—REPLACEMENT Option— 1 ............... 2 ............... Replace eight fuses having part number (P/N) 7918282–5503 with— New fuses having P/N 7918282– 5505. Modified and reidentified fuses having P/N 7918282–5505. Within 3,600 flight cycles after the effective date of this AD. Within 1,500 flight cycles after the effective date of this AD. (NARA). For information on the availability of this material at the 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 May 16, 2005. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–10428 Filed 5–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Note 1: Boeing Alert Service Bulletin 717– 32A0031 refers to Parker Hannifin Corporation Stratoflex Products Division Service Bulletin 836SD–8–6–20, Revision 1, dated June 23, 2004, as an additional source of service information for modifying and reidentifying the brake fuses. 14 CFR Part 39 Parts Installation (h) As of the effective date of this AD, no person may install a brake fuse, P/N 7918282–5503, on any airplane. Airworthiness Directives; Boeing Model 767–200, –300, and –300F Series Airplanes Alternative Methods of Compliance (AMOCs) (i) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 717–32A0031, dated September 10, 2004, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800– 0024). To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC. To review copies of the service information, go to the National Archives and Records Administration VerDate jul<14>2003 19:56 May 26, 2005 Jkt 205001 [Docket No. FAA–2004–19753; Directorate Identifier 2002–NM–264–AD; Amendment 39–14104; AD 2005–11–02] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 767–200, –300, and –300F series airplanes. That AD currently requires inspections for fatigue cracking of the horizontal stabilizer pivot bulkhead, and repetitive inspections or other follow-on actions. That action also provides a permanent repair, which is optional for airplanes with no cracks, and, if accomplished, ends the repetitive inspections. For airplanes on which the permanent repair is not installed, this new AD requires repetitive inspections of the same and additional inspection locations at new inspection intervals; a one-time torque test; and related investigative and corrective actions. For airplanes on which the permanent repair is installed, this new AD would require repetitive PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 inspections of the repaired area and, if necessary, corrective action. This AD is prompted by reports of loose tension bolts and crack indications in the fuselage skin. We are issuing this AD to find and fix fatigue cracking of the horizontal stabilizer pivot bulkhead and adjacent structure, which could result in loss of the horizontal stabilizer. DATES: This AD becomes effective July 1, 2005. The incorporation by reference of Boeing Alert Service Bulletin 767– 53A0078, Revision 3, dated November 15, 2001; and Boeing Alert Service Bulletin 767–53A0078, Revision 4, dated September 26, 2002, as listed in the AD is approved by the Director of the Federal Register as of July 1, 2005. On May 24, 2001 (66 FR 23538, May 9, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Service Bulletin 767–53–0078, Revision 2, dated April 19, 2001. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Docket: The AD docket contains the proposed AD, comments, and any final disposition. You can examine the AD docket on the Internet at https:// dms.dot.gov, or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Washington, DC. This docket number is FAA–2004–19753; the directorate identifier for this docket is 2002–NM– 264–AD. FOR FURTHER INFORMATION CONTACT: Suzanne Masterson, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 917–6441; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: The FAA proposed to amend part 39 of the E:\FR\FM\27MYR1.SGM 27MYR1

Agencies

[Federal Register Volume 70, Number 102 (Friday, May 27, 2005)]
[Rules and Regulations]
[Pages 30615-30617]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-10428]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-19987; Directorate Identifier 2004-NM-203-AD; 
Amendment 39-14105; AD 2005-11-03]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model 717-200 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain McDonnell Douglas Model 717-200 airplanes. This AD requires 
replacing eight brake fuses of the hydraulic quantity limiter with new 
or modified and reidentified fuses. This AD is prompted by reports 
indicating that brake fuses of the hydraulic quantity limiter of the 
main landing gear have failed. We are issuing this AD to prevent loss 
of both hydraulic and brake systems if one fuse on each hydraulic 
system were to fail simultaneously, and consequent reduced 
controllability of the airplane.

DATES: This AD becomes effective July 1, 2005.
    The incorporation by reference of a certain publication listed in 
the AD is approved by the Director of the Federal Register as of July 
1, 2005.

ADDRESSES: 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).
    Docket: The AD docket contains the proposed AD, comments, and any 
final disposition. You can examine the AD docket on the Internet at 
https://dms.dot.gov, or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at

[[Page 30616]]

the U.S. Department of Transportation, 400 Seventh Street SW, room PL-
401, Washington, DC. This docket number is FAA-2004-19987; the 
directorate identifier for this docket is 2004-NM-203-AD.

FOR FURTHER INFORMATION CONTACT: Albert Lam, 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) 627-5346; fax (562) 
627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with an AD for certain McDonnell Douglas Model 717-200 airplanes. That 
action, published in the Federal Register on January 5, 2005 (70 FR 
731), proposed to require replacing eight brake fuses of the hydraulic 
quantity limiter with new or modified and reidentified fuses.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
submitted on the proposed AD.

Support for Proposed AD

    One commenter supports the proposed AD.

Request to Refer to Vendor Part Numbers

    One commenter has no technical objection to the proposed AD, but 
would like the vendor part numbers to be included with the Boeing part 
numbers in paragraphs (g) and (h) of the proposed AD. The commenter 
provided no justification for its request.
    We do not agree. Paragraph (g) of the AD refers to Boeing Alert 
Service Bulletin 717-32A0031, dated September 10, 2004, as the 
appropriate source of service information for accomplishing the 
required replacement. Note (a) of paragraph 2.C.1. of the service 
bulletin identifies the vendor part numbers that correspond to the 
Boeing part numbers referenced in the AD. Therefore, we find it 
unnecessary to specify vendor part numbers in either paragraph (g) or 
(h) of the AD when the referenced service bulletin contains that 
information. We have made no change to the AD in this regard.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been submitted, and determined that air safety and 
the public interest require adopting the AD as proposed.

Costs of Compliance

    There are about 133 airplanes of the affected design in the 
worldwide fleet and 103 airplanes on the U.S. registry. The following 
table provides the estimated costs for U.S. operators to comply with 
this AD.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                        Average labor                                Cost per
                Action                   Work hours     rate per hour            Parts               airplane
----------------------------------------------------------------------------------------------------------------
Option 1. Replacement with new brake                9             $65  No Charge................            $585
 fuses.
Option 2. Replacement with modified                13              65  No Charge................             845
 and reidentified brake fuses.
----------------------------------------------------------------------------------------------------------------

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 have determined that 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD. See the ADDRESSES section for a location to 
examine the regulatory evaluation.

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 airworthiness 
directive (AD):

2005-11-03 McDonnell Douglas:
    Amendment 39-14105. Docket No. FAA-2004-19987; Directorate 
Identifier 2004-NM-203-AD.

Effective Date

    (a) This AD becomes effective July 1, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to McDonnell Douglas Model 717-200 
airplanes, fuselage numbers 5002 through 5134 inclusive; 
certificated in any category.

Unsafe Condition

    (d) This AD was prompted by reports indicating that brake fuses 
of the hydraulic quantity limiter of the main landing gear (MLG) 
have failed. We are issuing this AD to prevent loss of both 
hydraulic and brake systems if one fuse on each hydraulic system

[[Page 30617]]

were to fail simultaneously, and consequent reduced controllability 
of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Compliance Times

    (f) At the applicable time in Table 1 of this AD, do the action 
required by paragraph (g) of this AD.

                       Table 1.--Compliance Times
------------------------------------------------------------------------
         For airplanes having--                  Compliance time
------------------------------------------------------------------------
(1) Less than 5,000 total flight cycles  Within 3,600 flight cycles
 as of the effective date of this AD.     after the effective date of
                                          this AD.
(2) 5,000 or more total flight cycles    Within 1,500 flight cycles
 as of the effective date of this AD.     after the effective date of
                                          this AD.
------------------------------------------------------------------------

Replacement

    (g) Replace the eight brake fuses of the hydraulic quantity 
limiter by doing either Option 1 or Option 2 in Table 2 of this AD 
in accordance with Boeing Alert Service Bulletin 717-32A0031, dated 
September 10, 2004.

                          Table 2.--Replacement
------------------------------------------------------------------------
                                       Replace eight fuses having part
             Option--                 number (P/N) 7918282-5503 with--
------------------------------------------------------------------------
1.................................  New fuses having P/N 7918282-5505.
2.................................  Modified and reidentified fuses
                                     having P/N 7918282-5505.
------------------------------------------------------------------------


    Note 1: Boeing Alert Service Bulletin 717-32A0031 refers to 
Parker Hannifin Corporation Stratoflex Products Division Service 
Bulletin 836SD-8-6-20, Revision 1, dated June 23, 2004, as an 
additional source of service information for modifying and 
reidentifying the brake fuses.

Parts Installation

    (h) As of the effective date of this AD, no person may install a 
brake fuse, P/N 7918282-5503, on any airplane.

Alternative Methods of Compliance (AMOCs)

    (i) The Manager, Los Angeles Aircraft Certification Office 
(ACO), FAA, has the authority to approve AMOCs for this AD, if 
requested in accordance with the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (j) You must use Boeing Alert Service Bulletin 717-32A0031, 
dated September 10, 2004, to perform the actions that are required 
by this AD, unless the AD specifies otherwise. The Director of the 
Federal Register approves the incorporation by reference of this 
document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To 
get copies of the service information, contact Boeing Commercial 
Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). To view the AD docket, go to the Docket Management 
Facility, U.S. Department of Transportation, 400 Seventh Street SW., 
room PL-401, Nassif Building, Washington, DC. To review copies of 
the service information, go to the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at the 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 May 16, 2005.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 05-10428 Filed 5-26-05; 8:45 am]
BILLING CODE 4910-13-P
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